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<title cf:type="text"><![CDATA[Editorial department of the Journal of National University of Defense Technology -->航天工程]]></title>
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<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[The Numerical Simulation of the Supersonic External Flow over a Rearward Facing Step with Transverse Injection]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199002001]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[A jet stream injecting a supersonic external flow is a common technique for the f1ight control of an aerospace vehic1e. In this paper，MacCormack explicit scheme and Baldwin-Lomax algebraic turbulent model are employed to solve the 2D compressible RANS  equations for the numerical simulation of the supersonic external flow Over a rearward facing step with transverse injection. The   velocity vector field，pressure contour and Mach contour of the field are given. The step bottom pressure increases by about one   time as compared with the case without injection.]]></description>
<pubDate>2015/7/4 9:18:15</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Wang Zhenghua and Wang Chengyao]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Wang Zhenghua and Wang Chengyao</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199002001]]></guid><cfi:id>1087</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[CAD System for Joint Segment between Tow Stages of Sounding Rocket]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199002002]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[This paper develops a CAD  system (Hcadx) for stiffened waffle cylinder，supported by CADKEY as graphics system. The CAD system can    introduce user's operations by menu and can do buckling analysis of stiffened waffle cylinder by empirical formula or by analytic  method. It can also obtain optimal parameters by penalty function algorithm and may invoke CADKEY to plot design drawings of stiffened waffle cylinder automatically. It is not necessary to exit Hcadx. These design drawings can be edited easily to become acceptable work drawings.]]></description>
<pubDate>2015/7/4 9:18:15</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Li Guoguang and Huang Jianhua]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Li Guoguang and Huang Jianhua</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199002002]]></guid><cfi:id>1086</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[The Optimum Design of Flange-Stringers Panels]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199002003]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In this paper a flange-multistringer panel subjected to concentrated force is simplified into a model of a flange-stringer panel. The   optimum design method is set up by using the finite element method in strength analysis of the flange，and using the mathematical  programming method in structural synthesis. The results of numerical examples by this method indicate that the weight of the  structure decreases by 19.2% as compared with present design method under the same load.]]></description>
<pubDate>2015/7/4 9:18:15</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Li Shumin and Wang Zhonggang]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Li Shumin and Wang Zhonggang</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199002003]]></guid><cfi:id>1085</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[A General Solution for Solving Bending Problem of Simply Supported Rectangular Shallow Shell]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199002004]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[A general solution for solving elastic bending problem of simply supported rectangular shallow shells is established in this paper.  For example，the symmetric deformation for a simply supported rectangular shallow shell loaded uniformly with the displacement along   the four edges being zero，is solved.]]></description>
<pubDate>2015/7/4 9:18:16</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Huang Yan and Ren Junguo]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Huang Yan and Ren Junguo</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199002004]]></guid><cfi:id>1084</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[The Dynamic Characteristics Analysis of Flexible Liquid Storage Cylinder]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199002005]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In this paper，a re1iable and effective method for calculating the dynamic characteristics of fluid-filled cylindrical tanks is  developed. And the effect of the coupling between liquid sloshing and shell vibration is considered. The liquid is assumed to follow  the velocity potential theory，and the shell is modeled by the finite element method. In this approach，the number of unknowns is  substantially less than those in analyses where both tank wall and liouid are subdivided into finite elements.]]></description>
<pubDate>2015/7/4 9:18:16</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Liang Bo]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Liang Bo</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199002005]]></guid><cfi:id>1083</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Effects of High Altitude Slip Boundary Conditions on Chemical Non-equilibrium Viscous Shock-Layer flows]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199002006]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The numerical method is used for calculating the effects of slip boundary conditions on the viscous flows over blunt bodies at  different altitude The nonequilibrium viscous shock-layer equations are used as the governing equations，the boundary conditions   include shock-slip，wall-slip and no slip conditions. The numerical results show that the shock stand-off distance is thicker as slip  boundary conditions are considered，and the value of electron number density behind the bow shock is not zero. The numerical resu1ts  are pesented and compared with those from other methods.]]></description>
<pubDate>2015/7/4 9:18:16</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Shen Jianwei and Qu Zhanghua]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Shen Jianwei and Qu Zhanghua</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199002006]]></guid><cfi:id>1082</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Spline Finite Point Method for the Analysis of Nonlinear Dynamic Response of Beams and Plates]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199002007]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In this paper，the spline finite point method is presented for the geometrically nonlinear dynamic response of beams and plates based  on Berger hypothesis. The essential equations in the sp1ine finite point method are deduced and the incremental equations are solved   by means of wilson-θ method. The results show that the method in this paper can save computation time and make program simpler. As  compared with the finit element method，It can be easily carried out on personal computers.]]></description>
<pubDate>2015/7/4 9:18:16</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Wang Xinli and Zhang Renshu]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Wang Xinli and Zhang Renshu</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199002007]]></guid><cfi:id>1081</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[The General Expression for the Stability of Elastic Compressed Bars]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199002008]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The general expression for the stability of straight elastic compressed bars with constant cross section is derived in this paper.Seventeen equations for calculating the critical load of elastic compressed bars under various supporting conditions are all its special cases.]]></description>
<pubDate>2015/7/4 9:18:16</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Zhuo Shujun]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Zhuo Shujun</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199002008]]></guid><cfi:id>1080</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[A Method for Deducing the Formulas of the Range Angle and the Flying Time with the Elliptical Orbit]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199002009]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The range angle and the flying time for the passive section are calculated by using the quality with a constant vector in the  direction of the major axis of the elliptical orbit in this paper.]]></description>
<pubDate>2015/7/4 9:18:16</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Niu Yun]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Niu Yun</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199002009]]></guid><cfi:id>1079</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Liapunov Stability Criteria for Dual Spin Satellites with Flexible Appendages]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199103001]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The problem of attitude stability of dual spin sate11ites with flexible appendages is studied in this paper. The model of the flexible dual spin satellite consists of a semirigid platform with a semirigid axisymmetric rotor and n flexible appendages attached to it. The relative energy function of the system is selected as a Liapunov function in terms of the attitude angles and mode coordinates，and the attitude stability criteria is obtained by using the Liapunov stability theorem.]]></description>
<pubDate>2015/7/4 9:19:22</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Jin Liang]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Jin Liang</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199103001]]></guid><cfi:id>1078</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Kane's Equations of Flexible Multibody Systems with Tree Structure—— A Computer-Oriented Modeling Approach]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199103002]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The Kane's dynamical model of flexible multibody space systems with tree structure is developed in this paper. The system topology is  restricted to a tree configuration，which is defined as an arbitrary set of flexible and rigid bodies connected by hinges characterizing relative translations and rotations of two adjoining bodies. The relative translatioal velocities，angular velocities，and the differential of model coordinates are selected as the generalized velocities. The motion equations of minimum dimension are derived via Kane's method. The resulting equations are suitable for automatic generation，and simulated by computer.]]></description>
<pubDate>2015/7/4 9:19:22</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Jin Liang<sup>1</sup> and Helmut F.Bauer<sup>2</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Jin Liang<sup>1</sup> and Helmut F.Bauer<sup>2</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199103002]]></guid><cfi:id>1077</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[An Optimal Algorithm for Equilibrium Interfaces of Low-Gravity Liquids In the Spherical Tank with Space]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199103003]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[This paper presents a synthetic optimal algorithm for determining the equilibrium interfaces under low gravity conditions in the spherical tank with spacers. By means of this algorithm，the interfaces have been investigated in the range of 0.01-300 of bond numbers，0-90 degree of contact angles and 0.01-0.99 of liquid volume fractions. It is confirmed that the algorithm developed in this paper is convergent，efficient and correct.]]></description>
<pubDate>2015/7/4 9:19:22</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Zhao Zhijian and Wang Jinyu]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Zhao Zhijian and Wang Jinyu</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199103003]]></guid><cfi:id>1076</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Spallation Studies with Calculation]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199103004]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The dynamic fracture model proposed by J. N. Johnson is modified by considering materals work-harding and void nuc1eation. Numerial calculations of aluminium and OFCH copper spallation processes in its impact tests are carried on. The computation are in fair  agreement with the experimental results.]]></description>
<pubDate>2015/7/4 9:19:22</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Wang Zeping<sup>1</sup>, Yun Shourong<sup>1</sup> and Xie Fang<sup>2</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Wang Zeping<sup>1</sup>, Yun Shourong<sup>1</sup> and Xie Fang<sup>2</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199103004]]></guid><cfi:id>1075</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[An Analysis of Boundary Layer for Droplet Aerodynamic Stripped in High Speed Gas Flow]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199103005]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Based on the boundary layer theory in this paper，a theoretical model for the coupling problem of two phase boundary layer of gas and  droplet has been established. A formula to calculate the minimum velocity of gasflow needed to start the aerodynamic stripping  has been obtained for the problem of the aerodynamic stripping，which is a result from the interaction between gas and a droplet surface  when the droplet is in a high speed gas flow. This paper could be a useful to the investigation of atomizing mechanism of liquid fuel in high speed gas flow.]]></description>
<pubDate>2015/7/4 9:19:22</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Zhou Meng and Zhuang F. C.]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Zhou Meng and Zhuang F. C.</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199103005]]></guid><cfi:id>1074</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[The Application of Kantorovich Hybrid Method to the Plate Bending]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199103006]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Using the cubic B-Spline function as interpolation functions of stress and displacement，this paper has solved the bending problem of isotropic and anisotropic plate with modified complement energy principle and newly created kantorovich method.The method has advantages of high precision，rapid convergence and the convenience to deal with various boundary conditions. It has obtained stress solution with the same precision of displacement and does not exhibit locking effect and kinematic deformation mode，and is proved to be an effective method in solving bending problems of plate.]]></description>
<pubDate>2015/7/4 9:19:23</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Xu Houhua and Liu Xiaofeng]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Xu Houhua and Liu Xiaofeng</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199103006]]></guid><cfi:id>1073</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[The Technique of Vibration Diagnosis for Engineering Tube Failures]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199103007]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[This paper presents a new development of the technique of the identification equations of a failure diagnosis using frequency response  function (FRF) of the sensitive areas as an observed characteristics quantity (QCQ). It is obtained from sensitivity analysis of the  structure. The simualting calculation and experimental analysis of stiffness-type failure diagnosis for an engineering tube are made by Kalman filter iterative algoritm. The results show that the technique has greater accuracy and better antijam capability.]]></description>
<pubDate>2015/7/4 9:19:23</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Liu Ruiyan, Liu Yongjian and Qian PU]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Liu Ruiyan, Liu Yongjian and Qian PU</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199103007]]></guid><cfi:id>1072</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[A Well-posed Inversed Design Method for Transonic Airfoil]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199204001]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[From the Lighthill's exact solution for the incompressible inverse problem it is known that in the inverse design problem，the surface pressure distribution and the free stream speed can not be both prescribed independently. This suggests the existence of a constraint (regularity condition)on the pressure distribution. The same constraint exists at compressible speeds. In this paper，a well-posed inverse design method for transonic airfoil is presented. In the method，the target pressure distribution contains a free prameter  that can be adjusted during the computation to satisfy the regularity condition derived in this paper.]]></description>
<pubDate>2015/7/4 9:20:30</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Xia Zhixun<sup>1</sup> and Zhu Ziqiang<sup>2</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Xia Zhixun<sup>1</sup> and Zhu Ziqiang<sup>2</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199204001]]></guid><cfi:id>1071</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[The Formulations of Viscoelastic Poisson's Ratio]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199204002]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[This paper rewiews four formulations of viscoelastic Poisson's ratio，which are the formulation by differential operators，the formulation by hereditary integral and by complex and empirical methods. Also discused are the domain ralidty and problems of these methods，which provide convenient description of mechanical behaviors of solid rocket propellants.]]></description>
<pubDate>2015/7/4 9:20:30</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Hao Songlin]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Hao Songlin</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199204002]]></guid><cfi:id>1070</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[The Method of Perturbation-Harmonic Balance for Analysing Nonlinear Free Vibration of MDOF Systems and Structures]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199204003]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In this paper, the perturbation technique is introduced into the method of harmonic balance. A new method used for analysing  nonlinear free vibration of multidegree-offreedom systems and structures is obtained. The form of solution is expanded into a series  of Small parameters and harmonics, so no term will be lost in the solution and the algebric equations are linear. With the linear transformations，the matrices of the equations become diagonal. As soon as the modes related to linear vibration are found，the  solution can be obtained. This method is superior to the method of linearized iteration. The examples show that the method has high  accuracy for small amplitude problems and the results for rather large amplitude are satisfactory.]]></description>
<pubDate>2015/7/4 9:20:30</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Tang Qiangang and Sun Shixian]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Tang Qiangang and Sun Shixian</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199204003]]></guid><cfi:id>1069</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Analysis of Several Technical Problems in ZN-3 Sounding Rocket]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199204004]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The ZN-3 sounding rocket is an important instrument used for the sounding of space science. Because of its few using quantity and the  expensive scientific instrument it carries, not only high reliability is required, but also the advanced performance and econo mization are demanded. How to accurately deal with the relationship among these factors in technical design is very important.
In this paper，through analyses and discussions of correctly dealing with the technical problems，snchas the determinants of stage  number，formulatiog optimum program of thrust，reliability of construct and evaluation of fests etc. The methods unifying the general reliability，advancity and econom zation of the rocket are reached.]]></description>
<pubDate>2015/7/4 9:20:30</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Gan Chuxiong]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Gan Chuxiong</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199204004]]></guid><cfi:id>1068</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Using Spline Finite Point Method to Solve the Problem of Nonlinesr Dynamic Response of Plates]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199204005]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In this paper，the spline finite point methods is proposed to solve the problem of geometric nonlinear dynamic response of plates. Taking the form of the product of the cubic spline function and the mode shape function of beam，as trial function and starting from virtual displacement principle，the exact and explicit expression of nonlinear stiffness matrix is derived and the dynamic incremental equations are solved by means of wilson-θ method. The computational examples are given in this paper. Compared to the achievements  known，the method in it has following advantages: it leads to smaller amount of computational work，and 1t has higher accuracy. So the  spline finite point method is more effective in analyring nonlinear dynamic response of plates.]]></description>
<pubDate>2015/7/4 9:20:31</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Wang Xinli and Zhang Renshu]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Wang Xinli and Zhang Renshu</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199204005]]></guid><cfi:id>1067</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Analyses of Glide and Stability Performance of Controllable Parafoil Systems]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199204006]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The development of a controllable parafoil system provides the prospects for precise，undamagea recovery of large delicate payloads and recovery return systems intended for reuse. In this paper a six-degree-of-freedom flight dynamics model for such a system is  presented and the simulation program is developed to aid the study of system performance such as glide and dynamic stability etc. As  an example，the glide and dynamic stability performance of 40 (sqm) are a parafoil system has been discussed and some satisfactory results were obtained.]]></description>
<pubDate>2015/7/4 9:20:31</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Ge Yujun and Qin ZiZeng]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Ge Yujun and Qin ZiZeng</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199204006]]></guid><cfi:id>1066</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Analytical Method for Solving Bending Problem of Rectangular Plates on Elastic Foundations]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199202010]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[This paper gives a general solution of differential equation for solving bending problem of rectangular plates on elastic foundations. It can be used to solve the bending problem of rectangular plates with arbitrary edges under arbitrary load. For example, a square plate with four edges  free and loaded a concentrated load at the center is discussed.]]></description>
<pubDate>2015/7/4 9:20:07</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Huang Yan]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Huang Yan</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199202010]]></guid><cfi:id>1065</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Cycle Power Balance Analysis for Liquid Rocket Engine with LO<sub>2</sub>/RP-l Propellant Combination]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199202011]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The gas generator cycle and staged combustion cycle with LO<sub>2</sub>/RP-1 propellants combination have been analyzed in this paper. The  maximum combustion chamber pressure for various cycles has been found. The effect of combustion chamber pressure，sea level thrust，chamber mixture ratio，nozzle exit diameter on engine specific impulse and system balance parameters is given. The sensitivity dependences of effeciences，turbine pressure ratio，gas generator (or preburner) mixture ratio and other design parameters on balance parameters have been  investigated]]></description>
<pubDate>2015/7/4 9:20:07</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Chen Jie, Wang Kechang and Chen Qizhi]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Chen Jie, Wang Kechang and Chen Qizhi</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199202011]]></guid><cfi:id>1064</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[The Calculation and Analysis of the Launching Window of the FY-1B Weather Satellite on the Polar Orbit]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199202012]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In this paper，the Launching window of the FY-lB weather satellite on the polar orbit has been calculated by starting with its space  environment and conclusions with practical values have been obtained.]]></description>
<pubDate>2015/7/4 9:20:07</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Fan Zhenguo<sup>1</sup> and Lu Cilong<sup>2</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Fan Zhenguo<sup>1</sup> and Lu Cilong<sup>2</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199202012]]></guid><cfi:id>1063</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Newton Iterative Design Approach for Manned Spacecraft Ascent Trajectory]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199202013]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In this paper，the engineering design approach of manned spacecraft ascent trajectory is described. The mathematical model of control law is selected based on ascent flight property and flight dynamics principle. All the undertermined parameters are determined by using Newton iterative method based on ascent trajectory intermediate and terminal constraint conditions. Its flow chart is given and its correctness is proved by analog computation.]]></description>
<pubDate>2015/7/4 9:20:07</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Chen Kejun]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Chen Kejun</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199202013]]></guid><cfi:id>1062</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Realization of the Target Satellite Interception with Velocity Gain Guidance]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199202014]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[This paper is about the study of realization of the target satellite interception method with velocity gain guidance. The characteristics are  the following: based on the given conditions of the interceptor's initial motion parameters and the target's trajectory parameters，firstly the  predictive point of impact intercepting the target under the influence of J2 item of the earth oblatness is determined，then the interceptor's velocity required during the collision time using Lambert method is decided，at last，the target interception with velocity gain guidance method is realized. A transform condition with higher precision to the terminal guidance by using this method is guaranteed.]]></description>
<pubDate>2015/7/4 9:20:07</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Jia Peiran and Tang Guojian]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Jia Peiran and Tang Guojian</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199202014]]></guid><cfi:id>1061</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Biomechanical Tests and Analysis of Internal Fixation Used in Femoral Neck Fracture]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199202017]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In this paper，the axia1 compression-open disp1acement re1ation at the fracture point of the neck is tested for the femora1 neck of the body by three type of interna1 fixation pins (compression-screw，Steimann pin，triang1e pin). The axia1 compressioìl-twist ang1e of one cross section rotation to the other at the fracture point of the neck is a1so obtained. The performance of the three types of interna1 fixation stee1 pin are  compared，and the mechaniea1 ana1ysis of the interna1 fixation stee1 pin is given.]]></description>
<pubDate>2015/7/4 9:20:07</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Song Xiancun]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Song Xiancun</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199202017]]></guid><cfi:id>1060</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[A Approximate Method for Separating Strains in the Photoelastic Coatings]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199202018]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[A new method for separating principal Strains of photoelastic coatings has been presented in this paper. Drilling small holes in the coatings, in directions of principal strains, taking approximately the ratio of fringes at the hole edge equal to the ratio of principal strains，principal strains can be obtained. In the paper, the principle and approximate equation and typical experiment have been researched. The method  is visible and simple. It is shown that the method is easy to handle and practical value in engineering.]]></description>
<pubDate>2015/7/4 9:20:07</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Zhang Fan]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Zhang Fan</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199202018]]></guid><cfi:id>1059</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Introduction to the Data Processing of Throttling Rocket Engine Fire Test]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199202019]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[This paper introduces the data processing program in the fire test of the throttling rocket engine. The program is capable of processing both  static and dynamic performances of testing rocket engine，all the testing results (include data and plots) required can be provided in real-time. The extremely satisfactory results are obtaind in a number of tests.]]></description>
<pubDate>2015/7/4 9:20:08</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Yang Leping]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Yang Leping</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199202019]]></guid><cfi:id>1058</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[A Method of Calculating Elastic Curve of Semif1exible Plate Nozzle]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199202020]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[A method of calculating elastic curve for semiflexible plate wind tunnel nozzle has been presented，based on the linear theory of small  deflection of beam deformation，in this paper. In light of the match results of curvature between flexible plate calculated and  aerodynamic contour，the reasonable arrangment of jacks on the plate，which has an obvious effect on the curvature match，is of vital importance. So the structure designer of flexible nozzle should be cautious of it.]]></description>
<pubDate>2015/7/4 9:20:08</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Liu Mingjia]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Liu Mingjia</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199202020]]></guid><cfi:id>1057</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[New Directions of Liguid Rocket Engine Control]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199303001]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Many researches on liquid rocket engine (LRE) Control have been made to meet the needs for space flight missions，such as high propulsion performance，safety，reliability and low cost，Correspondingly，new directions and new fields of LRE control research have arisen，mainly focusing on health (condition) monitoring and intelligent control. This paper deals with the evolution of LRE intelligent control level，the  frameworks of health (condition) monitoring system and intelligent control system，the failure modes，the sensor technigues and the failure detection algorithms.]]></description>
<pubDate>2015/1/23 11:00:20</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Chen Qizhi]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Chen Qizhi</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199303001]]></guid><cfi:id>1056</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Trend of Solid Rocket propulsion Technology]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199303002]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In this paper，the trends of solid rocket propu1sion techno1ogy are discussed. It is necessary that the intercontinenta1 missiles be made small  sca1e and are 1aunched on an automobile，a train or a p1ane. So the main trend of SRM for intercontinental missi1e is to improve performance of SRM. In order to make anti-aircraft missiles tack1e the high-speed，high-maneuverab1e target，and to hide the missile site and missile itself，the main trend of SRM for anti-aircraft missiles is to develop the techno1ogy of controlled thrust and smoke1ess propellants. The main trends of boosters for 1aunch vehicles and SRM for small 1aunch vehicles are lower cost and higher re1iability. In addition，it is a1so an important tendency that the techno1ogy of SRM is app1ied to economica1 construction.]]></description>
<pubDate>2015/1/23 11:00:20</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Fang Dingyou]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Fang Dingyou</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199303002]]></guid><cfi:id>1055</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[The Creep Mechanics: its Past，Recent and the Prospect]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199303003]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Creep mechanics is an ancient as well as a young branch of solid mechanics. It is of practice and theoretical importance to the structure and  machine desiges in choosing the work-piece dimensions and estimating the effective service life of the heat-resisting parts, such as the  pressure vessels，pipings，turbine blands，or variously structural parts, protractedly operating under high-temperature, high pressure, and other harsh environments. The major task of creep research is to solve such knotty and severe engineering problems.
The present paper surveys and briefly reviews the major advances of creep mechanics. It inclucles four main parts:1 Historical activities on  creep mechanics；2.Some recent results in creep research；3.Several computational methods of stress analysis in common use；and 4.About creep rupture and failure.
We cherish the hope that it might be of some sevice to the youthful scholars and engineers.]]></description>
<pubDate>2015/1/23 11:00:20</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Zhou Mingxi and Hao Songlin]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Zhou Mingxi and Hao Songlin</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199303003]]></guid><cfi:id>1054</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[APPLICATION OF LINE-SPRING MODEL TO DYNAMIC FRACTURE OF ELASTIC-PLASTIC BEAM]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199303004]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The elastic-plastic line-spring model is proposed to analyse the dynamic fracture of a cracked beam of ductile material in present paper. It can be expected from the numerical results that this method for the analysis of dynamic fracture under elastic-plastic conditions will be valuable due to its computational simplicity.]]></description>
<pubDate>2015/1/23 11:00:21</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Lu Yinchu and Tang Guojin]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Lu Yinchu and Tang Guojin</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199303004]]></guid><cfi:id>1053</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[The Effects of Different Diffusion Models on Electron Distribution of Plasma Sheath about Reentry Bodies]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199303005]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The effects of different diffusion models are studied for electron distribution of plasma sheath about reentry bodies. The diffusion velocity of electron due to density gradients is much larger than that of ions because the weight of the electrons is about three orders in magnitude less  than that of the ions. Both the charge separation and its induced electric field exert an influence on the particle diffusion. The electron  density distribution is obtained with numerical solution under these conditions. The results are compared with other diffusion models such as  the quasi-neutral model，ambipolar diffusion model，etc. It shows that the quasi-neutral assumption is valid in most region of the flowfield，but the charge separation occurs near the body surface. The dimension of the thin layer with charge separation is in the same order of  Debye  shield length. The electric particle distribution is influenced somewhat by the boundary effects although the neutral moleculars and atoms are  unaffected. The applicability of these diffusion models is judged through their comparaision of the numerical solution.]]></description>
<pubDate>2015/1/23 11:00:20</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Qu Zhanghua,Shen Jianwei and Ruan Liming]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Qu Zhanghua,Shen Jianwei and Ruan Liming</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199303005]]></guid><cfi:id>1052</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[A Study of Evaporation of Liquid Propellant Droplet under High Pressure]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199302001]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The existing models of evaporation of liquid propellant droplet under high pressure have been modified by the authors. A submodel of solution of surrounding dielectric gas in droplet was developed to investigate the effect of solubility on evaporation under high pressure. A modified R-K equation of gas state was used in the model. Using the  model，the evaporation of propane droplet in a nitrogen environment was simulated. It was found that the evaporation time of droplet decreases with the increasing of pressure and environment temperature and that the droplet wi1l reach a supercritical state when the pressure is greater than a critical value. The solution of surrounding gas in droplet is very obvious under high pressure，and the higher the pressure，the greater the solubility. So it is important to take the effect of the solution into account in  high pressure combustion of propellant.]]></description>
<pubDate>2015/1/23 11:00:32</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Zhou Jin,Wu Daohong and Zhuang Fengchen]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Zhou Jin,Wu Daohong and Zhuang Fengchen</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199302001]]></guid><cfi:id>1051</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[The Pneumatic Computation of Aerobat with Steering Control Engines at the Base]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199302002]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In this paper，a new method is presented for the pneumatic computation of aerobat with steering control engines at the base. The method is an organic combination of S. C. Ward's engineering method and the axisymmetric numerical simulation method developed by the authors earlier for  the supersonic strong interaction flow field with transverse injection at the base. It can estimate the total propulsive forces and the  additional pitching and yawing momentum coefficients，including both direct and indirect parts. The base drag coefficient C<sub>D</sub> decreases as compared with the case without injection.]]></description>
<pubDate>2015/1/23 11:00:32</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Wang Zhenghua,Chen Lan and Wang Chengyao]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Wang Zhenghua,Chen Lan and Wang Chengyao</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199302002]]></guid><cfi:id>1050</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Velocity Control of Maneuvering Reentry Vehicle]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199302003]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In this paper，the problem of velocity control of maneuvering reentry vehic1e is described in detail. First，an optimal guidance law applied to attacking the fixed target is derived with the velocity directing to the ground. Second，the design methods of the ideal velocity curve design  and the detailed ways of controlling the falling velocity value are discussed. And it is proved by means of simulating computation that a considerable accuracy of falling velocity control has been obtained.]]></description>
<pubDate>2015/1/23 11:00:32</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Zhao Hanyuan and Chen Kejun]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Zhao Hanyuan and Chen Kejun</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199302003]]></guid><cfi:id>1049</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[The Estimation of Exterior Ballistic Measuring System Error for Missile Flight Test]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199302004]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[For missile flight test, telemetering data and exterior ballistic measuring data are the basis of precision and reliability analysis. Usually, we assume that exterior ballistic measuring error has normal distribution with zero mean. But during the real measuring, it is possible for exterior ballistic measuring parameters to cause system error. It has bad influence on the information obtained from flight trajectory and fall point. With the given model hypothesis, the estimation of exterior ballistic measuring system error is obtained in this paper. Futher more，some  simulating results and their preliminary analysis are given.]]></description>
<pubDate>2015/1/23 11:00:32</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Cai Hong and Jia Peiran]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Cai Hong and Jia Peiran</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199302004]]></guid><cfi:id>1048</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Analysis of Free Vibration of Conical Shell with Rigid Body of Large Mass]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199302005]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In this paper，the characters of a large-mass rigid body fixed to conical shell are considered. The displacement of the centre of mass and angular displacement of the body related to the displacement of nodal circle of finite element are obtained for each circumferential wave number. Comparing the results with those in actual motion，the correctness of the conclusion is demonstrated. This provides a theoretical foundation of dynamic analysis for the shells with rigid body of large mass.]]></description>
<pubDate>2015/1/23 11:00:32</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Tang Qiangang and Sun Shixian]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Tang Qiangang and Sun Shixian</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199302005]]></guid><cfi:id>1047</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Research of the Heat Transfer Characteristics of Micro Heat Pipe Used to Cool Electric Components]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199302007]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The experimental investigation of the heat transfer characteristics of the micro heat pipe used to cool the electronic components was presented in this paper. From the point of vlew of application，the concept of the maximum applicable power was proposed. The experimental results of the maximum applicable power vs. air velocity，wind temperature, mounting site and filling quantity of working fluid were given. In addition，the effect of using heat pipe for cooling modules was compared with that of using copper fin.]]></description>
<pubDate>2015/1/23 11:00:32</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Zhou Jizhu]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Zhou Jizhu</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199302007]]></guid><cfi:id>1046</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[A Overload Real Time Monitoring System with High Capabilities of Antijamming]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199302009]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[To monitor the vibration behavior of carrier vehicle in travel on line，a real time monitoring system has been developed. In this paper the  principle of operation and design features are discussed. Composition of the hardware and flow diagram of the software are given in detail. The  system has been applied in monitoring vibration overload of carrier vehicles of Asia and Ausat. The result shows that this system has achieved the expected design requirements and long-term stability and antijam features.]]></description>
<pubDate>2015/1/23 11:00:32</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Xie Liangpu,Song Xiancun and Su Mingzhao]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Xie Liangpu,Song Xiancun and Su Mingzhao</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199302009]]></guid><cfi:id>1045</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[The Fast Grid Generation Techniques of Elliptic Equation]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199302010]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In this paper，the grid generation techniques of elliptic equation are employed to generate curvilinear grids and the best difference scheme is obtained which allows fast convergence in numerical calculation by comparing four commonly used schemes. The conclusion is useful to the  numerical calculation of flow，and the boundary shape is dependent on time and the adaptive grid generation.]]></description>
<pubDate>2015/1/23 11:00:32</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Wu Jinxiang,Wang Zhenguo and Zhuang Fengchen]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Wu Jinxiang,Wang Zhenguo and Zhuang Fengchen</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199302010]]></guid><cfi:id>1044</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Application of CFD in Liquid Rocket Engine]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199404001]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[This paper overviews the application of computational fluid dynamics in liquid propellant rocket engine，presents its trends of development in future.]]></description>
<pubDate>2015/1/23 10:59:15</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Wang Zhenguo,Wu Jinxiang and Zhuang Fengchen]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Wang Zhenguo,Wu Jinxiang and Zhuang Fengchen</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199404001]]></guid><cfi:id>1043</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Solving Bending Problem of Rectangular Plates with Rest-on Edges by Distributed Point Method]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199404003]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In this paper the bending problem of thin rectangular elastic plates with rest-on edges is solved by general analytical solution of differential equations. The integral constants are determined by boundary conditions of the distributed point method. The square plates loaded symmetrically have been exemplified for analysis and calculation.]]></description>
<pubDate>2015/1/23 10:59:15</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Liu Daquan and Huang Yan]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Liu Daquan and Huang Yan</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199404003]]></guid><cfi:id>1042</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Zero Roll-Rate and Impact Dispersion of Ballistic Re-entry Missiles]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199403014]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[One of the greatest impact dispersion is caused by zero roll-rate for spinning missiles during their re-entry flights. The mechanism of roll-rate through zero is analysed. The altitude of zero roll-rate for including roll damping influence and the impact dispersion as a result of  zero roll-rate are formulaed. Finally，we compare six degrees of freedom simulation results of ballistic re-entry missiles motion with the  computing results of approximate formula. The comparison shows the feasibility of the approximate analysis.]]></description>
<pubDate>2015/1/23 10:59:30</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Huang Zhengui]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Huang Zhengui</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199403014]]></guid><cfi:id>1041</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Direct Measurements of Elastic Constants and Internal Damage in Composite Materials]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199403015]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In this paper，the elastic constants and damage evolution laws in composite materials are measured directly under one time loading condition with the assistant of micromechanics of composite materials and microcrack damage theory. The obtained results of the axial compression experiments of carbon Epoxy Composite cylinders are reasonable and reliable，and the direct measuring results can be convenicntly used to analyse the mechanical behavior and monitor the internal damage development in practical structure composite materials.]]></description>
<pubDate>2015/1/23 10:59:30</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Yang Guangsong,Zhu Hengwei and Lu Yinchu]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Yang Guangsong,Zhu Hengwei and Lu Yinchu</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199403015]]></guid><cfi:id>1040</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[9-DOF Simulation of Controllable Parafoil System for Gliding and Stability]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199402009]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In this paper，a 9-DOF (Degree of Freedom) flight dynamic model of controllable parafoil system is presented. Based on this  model，the simulation program is developed to aid the study of the gliding performance and dynamic stability for such a system with a parafoil of 40(sqm). Its results are compared with those of 6-DOF model. The stablitity of relative pitch is analysed in detail，and the methods for its improvement are given.]]></description>
<pubDate>2015/1/23 10:59:42</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Ma Hailiang and Qin Zizeng]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Ma Hailiang and Qin Zizeng</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199402009]]></guid><cfi:id>1039</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Application of Hill Equation in Long-distance Interception]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199402011]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[A method to reduce the model error of Hill equation in large relative distance case is proposed in this paper, by coordinate shifting to reduce   the large relative distance of original system to a small one in new system. That is, as the relative distance of interceptor is up to         ρ<sub>1</sub> (ρ<sub>1</sub> is defined as a controlled precision parameter, for example, ρ<sub>1</sub>=500km), an imaginary moving reference system with its origin at the interceptor's instantanious position is set up, thus the relative motion parameters of the interceptor in original system are translated into those in the new system (obviously the initial relative distance in the new system will be ρ<sub>(0)</sub>=0). As a result,the large distance problem becomes a small one，the describing precision of Hill equation is improved. This paper provides a theoretical analysis for this method and two examples of computer simulation.]]></description>
<pubDate>2015/1/23 10:59:41</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Chen Jianxiang]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Chen Jianxiang</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199402011]]></guid><cfi:id>1038</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[The Thermal Stress of the Solid Rocket Motor Grain in Storage]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199402012]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Stress analysis of solid propellant motor when temperature varys in storage is presented in this paper. A viscoelastic finite element model  based on integral creep constitutive relation is obtained and the method is applid to the thermal stress analysis of viscoelastic beam, cylinder and solid propellant motor.]]></description>
<pubDate>2015/1/23 10:59:42</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Feng Zhigang and Zhou Jianping]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Feng Zhigang and Zhou Jianping</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199402012]]></guid><cfi:id>1037</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Numerical Computation of Chemical Non-equilibrium Wakes]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199402013]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The analysis and computation of chemical non-equilibrium hypersonic wakes are important tasks of reentry aerodynamics. This paper，using axial  equations, successfully climinates the axial sigularity in governing equations. Using central differences secret scheme with two rand accuracy，it has solved the parabolic N-S equations and obtained numerical solutions of wakes at 20km and 60km，The results show that the effect of oxygen-electron attachment processes on electron density in far wakes is important.]]></description>
<pubDate>2015/1/23 10:59:42</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Chen Weifang,Shi Yuzhong and Wu Qifen]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Chen Weifang,Shi Yuzhong and Wu Qifen</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199402013]]></guid><cfi:id>1036</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Numerical Computation of Chamber-Nozzle Flowfield]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199401016]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The chamber-nozzle subsonic-transonic flowfield of solid rocket motor is computed by time-dependent method. The governing equations are  numerically solved by MacCormack explicit scheme. The parameters of boundary points are calculated with physical boundary conditions and  characteristic equations on the reference plane. It is shown that the numerical integral steps that have got to convergence for chamber-nozzle flowfield computation are much more than those for transonic nozzle flowfield calculation. Although the Mach number distribution along the wall  and axis for chamber-nozzle flowfield is similar to that for transonic nozzle flowfield，the iso-Mach number line distribution doesn't agree with the transonic nozzle flowfield.]]></description>
<pubDate>2015/1/23 10:59:57</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Zhou Chuanhui and Fang Dingyou]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Zhou Chuanhui and Fang Dingyou</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199401016]]></guid><cfi:id>1035</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[The Dynamical Behaviour Analysis of the van Der Pol Oscillator with the Negative Feedback]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199401017]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In this paper，the dynamical behaviour of the van der Pol oscillator with the negative feedback is studied based on the nonlinear dynamics and  the feedback control theory. The local stability and Hopf bifurcation behaviour are analysed by the center-manifold method and formal-Series method. The calculation results are brought about by Runge-Kutta method.]]></description>
<pubDate>2015/1/23 10:59:57</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Sun Pizhong]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Sun Pizhong</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199401017]]></guid><cfi:id>1034</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[INTELLIGENT DECISION ALGORITHM FOR FAULT DETECTION AND ITS APPLICATION]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199503005]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Based on statistical testing method of residuals or innovations such as Wald's SPRT criteria and the characteristics of neural networks，this paper proposes a new algorithm of fault detection for dynamic system，which is called intelligent decision algorithm. Because of relaxing the requirement on statistical properties of the systems，the algorithm has better robustness. The algorithm is applied to the fault detection for the liquid rocket engine with turbopump system，and simulation result shows that it is very effective.]]></description>
<pubDate>2015/1/23 16:03:15</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Wu Jianjun,Zhang Yulin and Chen Qizhi]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Wu Jianjun,Zhang Yulin and Chen Qizhi</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199503005]]></guid><cfi:id>1033</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[A BENDING DAMAGE THEORY FOR BEAMS UNDER PURE BENDING LOADS]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199503006]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Based on the basic assumptions of pure bending damage of beams，a simple bending damage theory is proposed, in which the definition of bending damage variable is defined by reduction of moment of inertia similar to that of tensile damage variable by reduction of loading area by L. M.  Kachanov (1958). For simplicity of application in engineering, the evolution law of bending damage variable can be adapted as a simple form. As an example, an exact bending damage analysis of a beam for creep pure bending is made. The calculating results are compared with the results obtained by Kachanov's tensile damage theory (1986). Moreover, in addition to determination by experiments (similar to the measurements of tensile damage, J. Lemaitre, 1987)，the material's constants of the simple bending damage model can be determined in first approximation to Kachanov's tensile damage model.]]></description>
<pubDate>2015/1/23 16:03:14</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Yang Guangsong,Lu Yinchu and Jin Xin]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Yang Guangsong,Lu Yinchu and Jin Xin</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199503006]]></guid><cfi:id>1032</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[THE CREEP-DAMAGE MODELING CORRELATED TO TEMPERATURE FOR COMPOSITE SOLID PROPELLANT]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199503015]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The creep-damage modeling correlated to temperature has been described for a kind of composite solid propellant (CSP) in this paper. The  material parameters of the modeling were determined by creep experiments of uniaxial and biaxial loading. The modeling is useful for analysis of solid rocket motor and for prediction of service life of the CSP.]]></description>
<pubDate>2015/1/23 16:03:16</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Shen Huairong]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Shen Huairong</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199503015]]></guid><cfi:id>1031</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[CALCULATION OF BURNING RATE CHARACTERISTICS IN ACCELERATED FIELD FOR SOME ALUMINIZED SOLID PROPELLANTS]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199503017]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In this paper the steady state combustion model of metalized propellants in an accelerated field is used to calculate the burning rate  characteristics of an aluminized HTPB propellant with two kinds of burning rate levels. A comparison between computational results and  experimental results of grain slabs on a spinning test stand is made. A discussion about some problems involved in calculations is presented.]]></description>
<pubDate>2015/1/23 16:03:16</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Cao Taiyue]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Cao Taiyue</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199503017]]></guid><cfi:id>1030</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Computational Model of Two-Phase Flow Spray Concentration Field in Coaxial Swirling Injector]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199502006]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In this paper，a computational model for simulating turbulent dispersion of droplets in two-phase flow spray field is presented. Liquid spray size distribution is divided into some droplets groups，which has a initial mass mean diameter differing from each other.All of the droplets in  same group have the same diameters，chemical components，temperature and velocity. The droplet turbulent disperse in the same group are  considered in the calculation. By comparisons it is demonstrated that calculated result is basically identical with tested result.]]></description>
<pubDate>2015/1/23 16:03:03</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Wang Zhenguo,Yan Xiaoqing and Liu Weidong]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Wang Zhenguo,Yan Xiaoqing and Liu Weidong</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199502006]]></guid><cfi:id>1029</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[In-plane Displacement Field Measuring Using Dynamic DSPI]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199502017]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In this paper，the method of measuring the in-plane displacement field under an impact loading is proposed and is named dynamic digital speckle pattern interferometry. By means of transient digital image capturing system，the undedeformed and deformed images are both stored directly in frame memory to achieve digital interfering. In the end of the paper，the in-plane displacement solution of a semi-infinite plane model is obtained experimentally，which shows good agreement with that by finite element method.]]></description>
<pubDate>2015/1/23 16:03:03</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Zhang Dongsheng<sup>1</sup> and Tong Jingwei<sup>2</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Zhang Dongsheng<sup>1</sup> and Tong Jingwei<sup>2</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199502017]]></guid><cfi:id>1028</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[A Creep Bending Damage Model on Beams]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199501012]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In this paper, based on the basic assumptions of pure bending damage of beams, the elementary equations are drived, in which the definition of  bending damage variable is defined by reduction of moment of inertia similar to that of tensile damage variable defined by reduction of loading area, a simple bending damage model is proposed similar to kachanov's tensile damage model. As an example, a bending damage analysis of a beam for creep pure bending is made, the material's constants of the simple bending damage model can be determined in first approximation to kachanov's tensile damage model，the calculating results are compared in good agreement with the results obtained by kachanov's tensile damage  model. It shows that the bending damage model is reasonable.]]></description>
<pubDate>2014/6/11 15:46:13</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Yang Guangsong,Jin Xing and Lu Yinchu]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Yang Guangsong,Jin Xing and Lu Yinchu</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199501012]]></guid><cfi:id>1027</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Wavelet Boundary Element Method]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199604001]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The functions on boundary are expanded into wavelet series，and the coefficient matrices are obtained from the values of kernal functions on the boundary using a circulant matrix method. The approximate solution of boundary integral equation is worked out by solving the unknown  wavelet coefficients. An example of 2D Laplace equation is given.]]></description>
<pubDate>2014/6/11 15:43:35</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Ren Junguo]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Ren Junguo</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199604001]]></guid><cfi:id>1026</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Fuzzy Direction Neural Network Approach to Fault Detection and Isolation of Rocket Engine]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199604002]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[A fuzzy direction neural network classifier used for fault detection and isolation (FDI) in a liquid propellant rocket engine is proposed. The fuzzy direction neural network utilizes fuzzy sets as engine fault classes. Each fuzzy set is an aggregate of fuzzy direction bodies. A fuzzy direction body is described by a direction vector，an included angle and two radii. The fuzzy direction neural network can learn nonlinear direction boundaries in a single pass through the training data. The FDI simulation research has shown the strong discernibility of the fuzzy direction neural network.]]></description>
<pubDate>2014/6/11 15:43:35</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Huang Minchao and Chen Qizhi]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Huang Minchao and Chen Qizhi</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199604002]]></guid><cfi:id>1025</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Heat Transfer Investigation of the Stratified Two-Phase Flow in Horizontal Tubes]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199604003]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The physical model and calculation motheds for the stratified two-phase flow in a horizontal condensation tube are investigated in this paper. The action of gravity and the effect of mass transfer on the interfacial shear are considered in this model.The program were used to calculate the flow and heat transfer characteristics of NH<sub>3</sub>-Al horizontal condensation tube and to give the axial profiles of parameters. The effects of flow rates and cooling conditions on this profiles were examined.]]></description>
<pubDate>2014/6/11 15:43:35</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Zhou Jizhu and Lv Zhixin]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Zhou Jizhu and Lv Zhixin</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199604003]]></guid><cfi:id>1024</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Structure  Analysis By Neural Network]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199604006]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[A feedback multi-layer neural network model is proposed for the structural analysis. The weight coefficients of middle-layer neural cells of the stiffness matrix given by finite element method using an exact integrated 4 node element. Numerical simulation shows that the method is consistent with FEM. This method presents a new way for the parallel structural analysis.]]></description>
<pubDate>2014/6/11 0:00:00</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Yi Xiaoshan,Ren Junguo and Zhou Jianping]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Yi Xiaoshan,Ren Junguo and Zhou Jianping</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199604006]]></guid><cfi:id>1023</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Calculation of the Automatical Optimizing Trajectory of Lunar Prober]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199604008]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The purpose of this paper is to solve the problem of designing optimized trajectory, based on the task that the prober is launched from the  anchorage orbit and lands on the moon. This paper emphasizingly discusses the design of automatical optimizing trajectory calculation of lunar prober. Finallly, simulation results show good standard trajectory.]]></description>
<pubDate>2014/6/11 15:43:35</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Xiao Qiying<sup>1</sup>,Huang Jiaomin<sup>1</sup>,Wang Zhengzhi<sup>1</sup> and Li Mingqiang<sup>2</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Xiao Qiying<sup>1</sup>,Huang Jiaomin<sup>1</sup>,Wang Zhengzhi<sup>1</sup> and Li Mingqiang<sup>2</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199604008]]></guid><cfi:id>1022</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[A Study on Soft-landing Orbit of Lunar Detector]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199604009]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In this paper，braking scheme and orbital optimization are discussed, assuming that the lunar detector approaches the moon vertically.]]></description>
<pubDate>2014/6/11 15:43:35</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Zeng Guoqiang,Zhao Hanyuan and Xi Xiaoning]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Zeng Guoqiang,Zhao Hanyuan and Xi Xiaoning</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199604009]]></guid><cfi:id>1021</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Numerical Simulation for Mass Flow Rate of Vortex Valve]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199604013]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The control properties of vortex valve for mass flow rate are numerically simulated. The time-dependent method is used to solve full Navier-Storkes governing equations. The calculation is made with the control mass added or not. The steady nozzle flowfield with vortex chamber is obtained and the nozzle mass flow rate is related with control mass flow rate. The results indicate that the vortex valve has good property for controlling nozzle mass flow rate.]]></description>
<pubDate>2014/6/11 15:43:36</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Liu Bing and Fang Dingyou]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Liu Bing and Fang Dingyou</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199604013]]></guid><cfi:id>1020</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Calculation of Aerodynamic Forces on the Vehicle and Grid-fins in the Complex Three-dimensional Fluid Field]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199603001]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[To calculate the aerodynamic forces on the vehicle and grid-fins，we use time-dependent method to solve the Navier-Stokes equation of ideal gas，and flux conservational multizones method to divide the complex vehicle and grid-fins into eight computational zones which are relatively  independent，and correlative with each other at once with satisfactory results.]]></description>
<pubDate>2014/6/11 15:43:21</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Yang Xiaohui and Wang Chengyao]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Yang Xiaohui and Wang Chengyao</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199603001]]></guid><cfi:id>1019</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Numerical Analysis of Combustion Processes of Hydrogen and Oxygen Jet in the Liquid Rocket Engine Preburner]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199603002]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In this paper，a comprehensive numerical model is presented for simulating combustion process of gas hydrogen and oxygen jet flow in the liquid   propellant rocket engine preburner，including the governing equations of combustion processes，k-εturbulece model，EBU turbulence combustion model and auxiliary formula of thermo-dynamic properties. With this model，numerical simulation of the effect of the injector configuration and  the jet mode of gas oxygen on the flow，mixing and combustion processes was performed. The numerical results show that the injector configuration and the jet mode of gas oxygen have a significant effect on flow field and combustion performance.]]></description>
<pubDate>2014/6/11 15:43:21</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Wang Zhenguo,Zhou jin,Yan Xiaoqing and Liu Weidong]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Wang Zhenguo,Zhou jin,Yan Xiaoqing and Liu Weidong</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199603002]]></guid><cfi:id>1018</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Numerical Simulation of Unsteady Flow in combustion Chamber of Liquid Propellant Rocket Engine]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199603003]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Numerical simulation of unsteady flow in liquid propellant rocket engine is performed with a new PISO algorithm in the present paper.The algorithm yields approximate solutions of the differential equation with one predictor step and two corrector steps at each time level instead of iteration calculation. Therefore，the CPU time cost in the calculation is reduced greatly which made numerical simulations of unsteady flow  become practicable.]]></description>
<pubDate>2014/6/11 15:43:21</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Liu Weidong,Wang Zhenguo,Zhou Jin and Zhuang Fengchen]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Liu Weidong,Wang Zhenguo,Zhou Jin and Zhuang Fengchen</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199603003]]></guid><cfi:id>1017</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Experimental Investigation of the Influence of Recess Ratio On the Atomization Properties of Coaxial Swirling Injectors]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199603004]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The Recess ratio (RR) is an important design parameter of gas-liquid coaxial swirling injector in liquid rocket engine. In this paper，an experimental investigation of the influence of RR on atomization properties of injectors has been carried out. The results show that there are certain differences between atomization properties of different injectors of different recess ratios under various working conditions. On the  whole，the recess ratio does not affect the atomization so obviously as it does on the flux and mixing ratio characteristics. At low gas   injecting drop，neither large RR nor small RR is favorable to atomization，on the contrary，both large RR and small RR will meliorate the  atomization at high gas injecting drop. However，with too large RR，the liquid injecting drop vibrates owing to the interaction of between and   liquid phases.]]></description>
<pubDate>2014/6/11 15:43:21</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Hu Xiaoping,Zhou Jin,Huang Yuhui and Wang Zhenguo]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Hu Xiaoping,Zhou Jin,Huang Yuhui and Wang Zhenguo</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199603004]]></guid><cfi:id>1016</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[The Quasi-Rigid Resolved Motion Control and Simulation for Free-f1oating Space Robot]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199603005]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The paper investigated the quasi-rigid resolved motion control for free-floating space manipulators when the base is not fixed，especially the  generalized Jacobin matrix applied, and one simulating example.]]></description>
<pubDate>2014/6/11 15:43:21</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Liu Xinjian<sup>1</sup>,Zhang Peng<sup>1</sup> and Tang Qiangang<sup>2</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Liu Xinjian<sup>1</sup>,Zhang Peng<sup>1</sup> and Tang Qiangang<sup>2</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199603005]]></guid><cfi:id>1015</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[A Study of Variation of Size and Structure of Pulverized Coal Particles in a Turbulent Jet Flame]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199603006]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[A turbulent coal jet flame is employed to simulate the rapid devolatilization of pulverized coal in practical coal combustion. The variation of the size and internal structure of coal particle during devolatilization were investigated through a sampling analysis technique. It is found that the volume of coal particles obviously expands during the devolatilization and the extent of the expansion heavily depends on the particle size and heating rate. During the devolatilization，the hollow structure of coal particles is formed due to the rapid release of volatile，which can result in more rapid combustion of char particles.]]></description>
<pubDate>2014/6/11 15:43:22</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Zhou Jin]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Zhou Jin</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199603006]]></guid><cfi:id>1014</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Numerical Simulation of 3-D Hypersonic Viscous Flowfield over a Capsule]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199602001]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The three dimensional hypersonic viscous flow of perfect gas over a capsule is calculated numerically. The Navier-Stokes equations are taken as the governing equations. The implicit NND scheme is used for the shock capture. The computation region is involved with the full flowfíeld from  the nose to the base. The flowfield properties and the areodynamic force coefficients thus obtained are good compared with the experiment results.]]></description>
<pubDate>2014/6/11 15:43:03</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Liu Jun and Qu Zhanghua]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Liu Jun and Qu Zhanghua</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199602001]]></guid><cfi:id>1013</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[DSMC Simulation of the Molecular Energy Transfer and Reaction by Collision]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199602002]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[This paper deals with the mechanism of molecular in elastic collision，presents the probability selective models of molecular internal excitation and molecular reactions，and introduces the energy transfer models among translational energy，rotational energy and vibrational energy. The results of the stagnation streamline flow of a hypersonic blunt body obtained by DSMC method conform with the results obtained by viscous shock layer (VSL) equation method at the lower altitude，which shows that models used in the DSMC simulation are appropriate.]]></description>
<pubDate>2014/6/11 15:43:03</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Chen Weifang,Shi Yuzhong and Wu Qifen]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Chen Weifang,Shi Yuzhong and Wu Qifen</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199602002]]></guid><cfi:id>1012</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[A Study of Landing Flare Manoeuvre Performance of Controllable Parafoil System for Spacecraft Recovery]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199602003]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[A large controllable parafoil can be used for spacecraft non-damage recovery at the planned-point. Its flare manoeuvre performance is of great importance to safe recovery. In this paper，a 4-DOF dynamic model of parafoil system for recovery is presented. The influence of system  parameters and flare manoeuvre control method on landing performance is discussed. The optimal system parameters and landing control method are given.]]></description>
<pubDate>2014/6/11 15:43:03</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Zhang Xiaojin]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Zhang Xiaojin</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199602003]]></guid><cfi:id>1011</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Viscoelastic Finite Element Analysis of a Cellular Plastic Bush]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199602004]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In this paper，the viscoelasitc finite element analysis program used for a polyurethane cellular plastic bush is discussed. Stress relaxation in the axisymmetric bush is calculated by utilizing integral constitutive relation. It can be seen from the numerial results that the assembling stress relaxes by about 25% after the bush has been stored by 1000 hours.]]></description>
<pubDate>2014/6/11 15:43:03</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Shen Huairong and Hao Songlin]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Shen Huairong and Hao Songlin</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199602004]]></guid><cfi:id>1010</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[An Analysis of Preforce in the Locking Device of the Satellite and Launching Vehicle with Wrapband]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199602005]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[According to the force of connecting place and feature of the locking device，the possibilities of loosening in the connecting place of the  satellite and launching vehicle are studied in this paper. The formulae of preforce the wrapband needs are obtained by applying the theory of a general force system and friction. The distribution of wrapband stress is analysed，and the method for solving the nonuniform distribution of the stress is put forword. Compard with the experimental results of the two types of the device，it is proved that the method of analysis and  the formulae of calculation are reliable. The conclusions provide a basis for designing the locking structure of a satellite and launching vehicle with wrapband.]]></description>
<pubDate>2014/6/11 15:43:03</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Tang Qiangang and Sun Shixian]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Tang Qiangang and Sun Shixian</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199602005]]></guid><cfi:id>1009</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Numerical Simulation for Whole Target Flow Field and Electronic-Radiant Characteristic of Small Blunted Cone]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199601001]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Adopting the models of chemical non-equilibrium and radiant nonequilib-rium，according to simplified or full Naver-Stokes equation，We  numerically simulates whole target flow field and electronic-radiant characteristic of small blunted cone having ablative material injection with the purpose of providing the aero-physics data for protective design. The simulative results of flow field are compared with experimental data and good agreements are found. The numerical results show that the wall ablative material injection and the wall catalytic characteristic are considered，and have orders influence to electronic number density.]]></description>
<pubDate>2014/6/11 0:00:00</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Cao Dengtai,Shi Yuzhong,Chen Weifang and Wu Qifen]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Cao Dengtai,Shi Yuzhong,Chen Weifang and Wu Qifen</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199601001]]></guid><cfi:id>1008</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Experimental Investigation on Spray Characteristics of Coaxial Swirling Injector]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199601002]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In this paper, an experimental investigation on spray characteristics of coaxial swirling injector was performed using the laser-scattering  system (Malvern) and the self-designed atomization and sprays test facility. It was analyzed and discussed that the effect of gas injecting  pressure differential on the spray mass median diameter (MMD) and spray diameter size distribution exponent (n). The study results should provide theoretic guidance in on going gas-liquid coaxial swirling injector design.]]></description>
<pubDate>2014/6/11 15:42:49</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Wang Zhenguo,Zhou Jin,Yan Xiaoqing and Wu Jinxiang]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Wang Zhenguo,Zhou Jin,Yan Xiaoqing and Wu Jinxiang</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199601002]]></guid><cfi:id>1007</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Numerical Simulation of Turbulent Internal Flowfield in Solid Rocket Motor]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199601003]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The governing equations are the compressible full Navier-stokes equations. Maccormack's time-dependent explicit scheme is used to solve  axisynmetric internal flowfield of the solid propellant rocket motor. A turbulent model based on the Bald-win-lomax algebraic scheme is employed to get the coefficient of turbulent viscosity. The solution of the internal flowfield for the soliel rocket motor with tube grain is obtained. The results are satisfactory. The methods are of reference value to the engineering design of SRM.]]></description>
<pubDate>2014/6/11 0:00:00</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Jiao Shaoqiu,Fang Dingyou and Zhang Weihua]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Jiao Shaoqiu,Fang Dingyou and Zhang Weihua</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199601003]]></guid><cfi:id>1006</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Researches for Beam's Fault Diagnosis Based on Neural Network and Fuzzy Synthetic Judgement]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199601004]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[A simple artificial intelligence system for fault diagnosis established in this paper. The system consists of knowledge base，fuzzy reasoning module，neural network module and control module. The fault pre-diagnosis is completed in the fuzzy reasoning module by use of fuzzy synthetic  judgement method. The identification of the fault types is achieved in the neural network module using competitive learning algorithm. The  seven models for the single and composite. faults of a cantilever beam have been investigated. The results are satisfactory.]]></description>
<pubDate>2014/6/11 15:42:49</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Han Xiaoyun and Liu Ruiyan]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Han Xiaoyun and Liu Ruiyan</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199601004]]></guid><cfi:id>1005</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Decentralized Multilevel Vibration Control of Large Flexible Space Structures]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199601005]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Using multilevel control method. we studied the coupling active control of the large flexible structures in this article. Taking the dynamic variables of structure as the system states directly, the feedback gains of this vibration system have been developed. According to the theory presented in this article, one space station model has been taken as an illustrated example. The computer simulation has been carried out and the satisfactory results have been gotten. Theoretical and numerical results show that the method presented in this article is of many special advantages to the vibration system of large flexible structures.]]></description>
<pubDate>2014/6/11 15:42:49</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Lin Xiqiang and Li Dongxu]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Lin Xiqiang and Li Dongxu</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199601005]]></guid><cfi:id>1004</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[The Theory of Magneto-hydrodynamic Linear Stability Condition of Biadiabatical Approximation]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199601006]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[This paper has given magneto-hydrodynamic energy integration relationship at the condition of biadiabatical approximaticn. Analysis shows that  magneto-hydrodynamic system of this kind is conservative. It is feasible to adopt kinetic equations or method of energy principle to analyze the  systematic stability. This paper has discussed the basic principle of linear stability proceed from governing equations，and has showed that  increment of longitudnal pressure is benifit to systematic stability.]]></description>
<pubDate>2014/6/11 0:00:00</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Wu Qifen and Shi Yuzhong]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Wu Qifen and Shi Yuzhong</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199601006]]></guid><cfi:id>1003</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[The Application of Parametric Differentiation for Extracting Resistance Coefficients from Firing Test Data]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199601009]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[This paper mainly discusses the procedure of applying paramctric differentiation to extract resistance coefficients. The computer simulation results are presented. This method has been actually applied in shooting range.]]></description>
<pubDate>2014/6/11 0:00:00</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Wan Jianwei,Zhou Liangzhu and Huangfu Kan]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Wan Jianwei,Zhou Liangzhu and Huangfu Kan</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199601009]]></guid><cfi:id>1002</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Time-Effect of Vibro-Acoustics on the Pressure-Vessel-The Investigation of Sound Excitation]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199601011]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The requirement of the time-effect of vibro-acoustics for the distribution of the dynamic stress and the structural characteristics of the   pressure vessel are first explored. By analyzing its modal parameters and dynamic stress，a new method of sound excitation is given for  eliminating the welding residual stress to achieve the time-effect. It is proved successful in practice.]]></description>
<pubDate>2014/6/11 15:42:49</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Su Mingzhao and Shang Jingming]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Su Mingzhao and Shang Jingming</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199601011]]></guid><cfi:id>1001</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Recent Development in Submunition]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199601012]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In this paper，some recent development in submunition and dispenser is summarized. Its characteristics and the trend of the development are  presented. Further-more，some key technique is preliminarily discussed.]]></description>
<pubDate>2014/6/11 15:42:49</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Zheng Rongyue and Qin Zizeng]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Zheng Rongyue and Qin Zizeng</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199601012]]></guid><cfi:id>1000</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Characteristics and Approximate Solutions of Normalimpact Transfer Trajectory to the Moon]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199706001]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[A patched-conic technique is used to formulate the mathematical model and to make an explicit analysis of the normal-impact transfer trajcctory to the moon. Some approximations are required in order to obtain the analytical solutions of the normal-impact transfer trajectory to the moon. It is a practical engineering method for preliminary trajectory designing.]]></description>
<pubDate>2014/5/28 9:49:23</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Ren Xuan<sup>1</sup> and Chen Jianxiang<sup>2</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Ren Xuan<sup>1</sup> and Chen Jianxiang<sup>2</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199706001]]></guid><cfi:id>999</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[An Approach to High Power Laser Interaction with Gas Filling Light Copying Decoy]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199706002]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In the light of structural characterstics of gas-filling light-copying decoy，we discuss high power laser interation with gas-filling light-copying decoy，and the change of decoy motion velocity after decoy is attacked by high power laser. Besides，its trajectory deflection has been calculated.]]></description>
<pubDate>2014/5/28 9:49:23</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Zhao Jiankang]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Zhao Jiankang</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199706002]]></guid><cfi:id>998</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Fuzzy Rule Sets Approach to Engine Fault Diagnosis]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199706004]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Based on the fuzzy measuring of fuzzy rule sets，a scheme system used for fault diagnosis is proposed in this paper. The extraction of fuzzy  rules involves two steps: (1) the whole space of the trained data is adaptively divided into subspaces in the form of hypersphere. It is probable to solve the problems of recognition in the high dimension space. (2) A fuzzy rule in each subspace is generated and confidence of each fuzzy rule calculated. We extend the conception of the traditional fuzzy rule for the purpose of resolving the contadictions among the  generated fuzzy rules. The simulation research has shown that the fuzzy measuring of the fuzzy rule sets can be used for the fault diagnosis  of the liquid rocket engine.]]></description>
<pubDate>2014/5/28 9:49:24</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Huang Minchao and Chen Qizhi]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Huang Minchao and Chen Qizhi</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199706004]]></guid><cfi:id>997</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Analysis and Estimation of Shooting Probability of Submunition Attacking Large Object]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199706005]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Shooting probability is an important parameter of submunition efficacy. In this paper. a simple approximate method is given for calculating percentage of hits of submunition attacking large (linear) object. The calculating results show that approximate method is of computational advantage and the results are satisfactory. Then the concept of block probability of submunition is introduced and discussed in this paper.    The results would be useful reference for further research of submunition.]]></description>
<pubDate>2014/5/28 9:49:24</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Tang Jian,Qin Zizeng and Zheng Rongyue]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Tang Jian,Qin Zizeng and Zheng Rongyue</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199706005]]></guid><cfi:id>996</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[An Approach to Spacecraft Returning Reentry Guidance]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199706006]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In this paper，an approach to spacecraft returning reentry guidance is described. The composite shutdown guidance scheme is put forward in the  paper，which is applied to decrease reentry state parameters error caused by retro-error in returning phase. And then，reentry guidance law is studied. Finally，it's correctness is proved by simulation.]]></description>
<pubDate>2014/5/28 9:49:24</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Chen Kejun]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Chen Kejun</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199706006]]></guid><cfi:id>995</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Parallel High-order Dense Matrix Inversion and Applications]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199704001]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In this paper we propose Gauss-Jordan algorithm using column interchanges for computing a high-order dense matrix inverse produced by the high-order panel method in aerodynamics. The algorithm implements the block cyclic data distribution, which especially has communication advantages for the hypercube network. Results are achieved when running this program on the 4 SGI workstations configured as a 2×2 processor grid. It shows that 57%～64% efficiency can be gained when solving a matrix is about 1000 order.]]></description>
<pubDate>2014/5/28 9:47:41</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Chen Jun,Wang Zhenghua and Li Xiaomei]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Chen Jun,Wang Zhenghua and Li Xiaomei</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199704001]]></guid><cfi:id>994</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Numerical Simulation of Vibration-Nonequilibrium Nozzle Flow]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199704002]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The quasi-one-dimensional vibrational-nonequilibrium nozzle flow of nitrogen gas is calculated numerically by using a time-dependent analysis. The explicit MacCormack scheme is used for the numerical solution. The vibrational-nonequilibrium effects of various flow parameters have been discussed and the important factor has been found. It is shown that for some practical nozzle conditions, the vibrational-nonequilibrium effects have significant influence on the freestream nozzle-flow properties.]]></description>
<pubDate>2014/5/28 9:47:41</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Huang Hua,Qu Zhanghua,Liu Jun and Zeng Ming]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Huang Hua,Qu Zhanghua,Liu Jun and Zeng Ming</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199704002]]></guid><cfi:id>993</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[A Study of the Mixing Characteristics of Gas-Liquid Coaxial Swirling Injector of Liquid Rocket Engine]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199704003]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[This paper presents an experimental study on the mixing characteristics of gas-liquid coaxial swirling injector of liquid rocket engine. A two-phase probe technique was employed to measure the distributions of gas and liquid mass flux and mixing ratio in sprays. The effects of the recess ratio of injector and the pressure drop of gas and liquid injection on the mixing characteristics were investigated. The results show that the recess ratio of injector plays a significant role in the mixing between gas and liquid flows from the coaxial swirling injector . Increasing the recess ratio will result in more uniform mixing between gas and liquid, and changing the pressure drop of injection will result in different distribution of mass flux and mixing ratio.]]></description>
<pubDate>2014/5/28 9:47:41</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Zhou Jin,Hu Xiaoping,Huang Yuhui and Wang Zhenguo]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Zhou Jin,Hu Xiaoping,Huang Yuhui and Wang Zhenguo</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199704003]]></guid><cfi:id>992</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Dynamic Characteristic and Separation Behavior Analysis for Satellite Fairing]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199704005]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[This paper gives the structural dynamic FEM model and corresponding FEM software package for a certain honeycomb sandwich composite satellite fairing. The natural frequencies and modes of the whole and half fairing under different boundary conditions are calculated. The separation behavior of half fairing and the load distribution in all binder blots subjected to aerodynamic load are analyzed.]]></description>
<pubDate>2014/5/28 9:47:42</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Lei Yongjun,Zhuo Shujun,Zheng Rongyue and Ren Junguo]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Lei Yongjun,Zhuo Shujun,Zheng Rongyue and Ren Junguo</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199704005]]></guid><cfi:id>991</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Optimal Power-driven State Tracing of Module in Brake]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199704006]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In this paper according to the equation of movement of the lunar module, under the condition of fixed thrust, the optimal direction of thrust is obtained. Along such a dirction, a self-adapting adjustment control is given to the perturbation equation to guarantee the stability of state-tracing, so as to assure the high precision of the output tracing state for the system under control.]]></description>
<pubDate>2014/5/28 9:47:42</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Xue Zhengsheng,Hu XiaoPing and Chen XinHai]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Xue Zhengsheng,Hu XiaoPing and Chen XinHai</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199704006]]></guid><cfi:id>990</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Control of vibro-acoustical load and time of pressure-vessel by vibro-acoustics ageing]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199704008]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In the paper, vibro-acoustical load and time of pressure-vessel by vibro-acoustic ageing are investigated through the experiments on pressure-vessels and the control approach and criteria of the quality of vibro-acoustic ageing are obtained. The results of the application, the approach and criteria into the pressure-vessels are satisfying.]]></description>
<pubDate>2014/5/28 9:47:42</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Xie Liangpu and Shang Jinming]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Xie Liangpu and Shang Jinming</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199704008]]></guid><cfi:id>989</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[An Approach to the Supersonic Complex Fluid Field Calculation of Vehicle at the Discontinuous Profile Lines]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199703012]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Finite-Volume method was used to solve the three-dimensional Navier-Stokes equations of ideal gas, and combine flux conservative patched method and B-L turbulence model correction to study this problem, capturing fluid field informations such as separation vortex, shock wave, expansion wave.]]></description>
<pubDate>2014/5/28 9:47:29</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Yang Xiaohui and Wang Chengyao]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Yang Xiaohui and Wang Chengyao</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199703012]]></guid><cfi:id>988</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[A Sort of Inspecting Method for Nonlinear Vibration in Structural Model Test and Its Application]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199703013]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In this paper, based on the principle of Hilbert connection for real and imaginary part of vibration signals, the inspecting technique for nonlinear vibration was developed. In accordance with the special characteristics of engineering structure, a sort of fast algorithm and correction technique was used. By application in a fairing of rocket, it was proved practicable.]]></description>
<pubDate>2014/5/28 9:47:30</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Tan Zhiyong<sup>1</sup> and Zhang Dongsheng<sup>2</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Tan Zhiyong<sup>1</sup> and Zhang Dongsheng<sup>2</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199703013]]></guid><cfi:id>987</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[The Analysis of the Effects of the Dry Mass of Single-Stage-to-Orbit Vehicle]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199703018]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[A method to calculate the dry mass of single-stage vehicle is proposed in this paper. A baseline vehicle is presented for the given flight mission, and the effects of the tank material, the thermal protection system and the design margin on the vehicle dry mass are calculated. The calculation results show that the advanced material and design can decrease the vehicle dry mass and its sensitivity to the design margin.]]></description>
<pubDate>2014/5/28 9:47:30</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Huang Weidong,Wang Kechang and Chen Qizhi]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Huang Weidong,Wang Kechang and Chen Qizhi</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199703018]]></guid><cfi:id>986</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Analysis of the Effects of Internal and External Interfering Factors on the Liquid Rocket Engine]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199703019]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Based on the nonliear mathematical model for the steady state operation of a liquid rocket engine, the effects of each interfering factor on the parameters of liquid rocket engine are calculated. The comparative analysis is carried out for the effects of the interfering factors on the engine parameters by using both nonlinear method and method of small deviations. The results obtained can be used for the analysis of the pump-fed gas generator cycle liquid rocket engine test results，the reliability analysis and the fault analysis, and also for bringing to light the variation of the engine parameters with various interfering factors.]]></description>
<pubDate>2014/5/28 9:47:30</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Shen Chibing,Wu Jianjun and Chen Qizhi]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Shen Chibing,Wu Jianjun and Chen Qizhi</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199703019]]></guid><cfi:id>985</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Sound Insulation Model and Analytic Calculation for Flying Thin Structure]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199702001]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The sound insulation analysis model is presented in terms of sound insulation theory and practical engineering for the sound insulation problem of flying thin shell with complicated configration and special organization. It is compared with the measurement of the simulated shell by calculation. The results showed that the presented sound insulation analytic method and the model are correct and feasible The calculation can be used to evaluate the sound insulation ability for flying structure.]]></description>
<pubDate>2014/5/28 9:47:09</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Liu Xinjian,Tang Qiangang and Sun Shixian]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Liu Xinjian,Tang Qiangang and Sun Shixian</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199702001]]></guid><cfi:id>984</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Optimization Analysis of the Locality of Attitude Control Engines for Spacecraft]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199702002]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Based on the mass models of the liquid propellamt engine thrust system, an approach has been presented for the optimization of the locality arrangement of the bipropellant attitude control engines. The optimization objective function is the total mass of the smallest thrust system, while the restrictive condition is that the total efficient control impulsion and total efficient control impulsion moment are certain.]]></description>
<pubDate>2014/5/28 9:47:09</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Hu Xiaoping,Wang Zhongwei,Zhang Weihua and Wang Zhenguo]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Hu Xiaoping,Wang Zhongwei,Zhang Weihua and Wang Zhenguo</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199702002]]></guid><cfi:id>983</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Combustion Instability of the Liquid Rocket Engine and the Mechanism of Sound Amplification by Heat Release]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199702003]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[high frequency instability in liquid rocket engine is simulated by the method of computational fluid dynamics. The gas controlling equations are described under the Euler coordinate. The liquid phase controlling equations are described under the Lagrangian coordinate. The turbulence model is κ-ε model of high Reynolds number. To assess the combustion instability, the sinusoidal pulse is put into the combustor. The calculated results are observed by the way of Rayleigh mechanism of sound amplification by heat release. The curve of combustion stability is plotted to various perturbation and initial droplet diameter.]]></description>
<pubDate>2014/5/28 9:47:10</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Zhao Wentao<sup>1</sup>,Zhou Jin<sup>1</sup>,Nie Wansheng<sup>2</sup> and Zhuang Fengchen<sup>2</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Zhao Wentao<sup>1</sup>,Zhou Jin<sup>1</sup>,Nie Wansheng<sup>2</sup> and Zhuang Fengchen<sup>2</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199702003]]></guid><cfi:id>982</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[The Analytical Study on Enviromental Contamination of the Space Station and Its Simulation Modulars]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199702004]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[On the basis of defining the definite conception of enviromental contamination of the space Station, the contamination sources consist of self-contamination, plume contamination and partical cloud contamination according to the causes of contamination. The respective analytical modes for prediction of potential contamination that would be applied to developing simulation modular for external contamination analysis is presented with its own formation mechanism. For the more serious plume contamination, source overall disposal is suggested to construct a project of modular simulation together with modeling construction, alogrithm, numerical simulation of flowfields and the analysis of the effects of contamination to apply to space station design and to develop an applicable contamination control system.]]></description>
<pubDate>2014/5/28 9:47:10</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Ren Bing,Huang Lin and Sun Fei]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Ren Bing,Huang Lin and Sun Fei</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199702004]]></guid><cfi:id>981</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Analysis of Dynamic Fracture of Three-Point Bending Beam]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199702018]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In this paper, a new method of dynamic fracture analysis of three-point bending beam with an edge crack is presented by applying the elementary bending theory of beam and the line-spring model. This method can simplify calculation, and the numerical results show that it has high precision.]]></description>
<pubDate>2014/5/28 9:47:11</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Tang Guojin and Zhou Jianping]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Tang Guojin and Zhou Jianping</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199702018]]></guid><cfi:id>980</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[The Variational Principle of Stability of Thin Shells]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199702022]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[This paper gives the resultant forces and moments, strain energy and the work of the external forces on the basis of the deformation theory of flexible body. In accordance with the principle of virtual displacement, the energy criterion of critical load is obtained and the equilibrium diffenential equations and boundary conditions of stability problem are derived. The formula is discussed and simplified.]]></description>
<pubDate>2014/5/28 9:47:11</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Huang Yan]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Huang Yan</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199702022]]></guid><cfi:id>979</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[A Quick Model for Calculation of the Exhaust Plumes]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199701001]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[A quick calculation method for evaluation of the exhaust plumes of the rocket motors, and the effects of the exhaust plumes on the flow field around the rocket are considered. In this model, the impingement between the plumes and the surface is calculated with the Newton's theory, furthermore the disturbance between the free flow and the plumes is also considered. The results show that the method is useful for the design of spacecraft.]]></description>
<pubDate>2014/5/28 9:46:38</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Xia Zhixun,Fang Dingyou,Zhang Weihua and Yang Tao]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Xia Zhixun,Fang Dingyou,Zhang Weihua and Yang Tao</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199701001]]></guid><cfi:id>978</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Bayesian MAP Estimation of Noise Statistics and System Adaptive Filtering]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199701002]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[For linear discrete systems with unknown noise statistics, the Bayesian maximum a posteriori (MAP) estimation of noise statistics are its real-time approximation are deduced considering that the prior information of noise statistics is normal-inverted-Wishart distribution. Based on this, the system adaptive filtering is obtained.]]></description>
<pubDate>2014/5/28 9:46:38</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Cai Hong]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Cai Hong</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199701002]]></guid><cfi:id>977</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Approximate Solution of the lnfinite Body with an Embedded Elliptic Crack of Power Hardening Material]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199806001]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The fully plastic J-integral of the embedded elliptic crack, on which the uniform pressure is exerted, in the infinite body of power hardening material is derived cleverly by use of energy method in this paper. The fully plastic J-integral is a simple analytic form. The solving process is base on the solution of HRR<sup>[1,2]</sup>.]]></description>
<pubDate>2014/1/3 16:01:51</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Tang Guojin,Yuan Jiehong and Zhou Jianping]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Tang Guojin,Yuan Jiehong and Zhou Jianping</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199806001]]></guid><cfi:id>976</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[The Parallel Numerical Simulation of 3-D Supersonic Blunt Body Base Flow in PVM and Flow's Topology Analysis]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199806002]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[This paper uses patched grid method to divide grids and parallel software platform PVM based on message-passing to distribute computational task. The large scale parallel numerical simulations of 3-D supersonic blunt body base flow are accomplished. The results show that the pressure characteristics in base are coincident with experimental results and base flow's topological configurations are reasonable.]]></description>
<pubDate>2014/1/3 0:00:00</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Yang Xiaohui<sup>1</sup>,Wang Zhenghua<sup>1</sup>,Liu Zhong<sup>1</sup> and Wang Chengyao<sup>2</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Yang Xiaohui<sup>1</sup>,Wang Zhenghua<sup>1</sup>,Liu Zhong<sup>1</sup> and Wang Chengyao<sup>2</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199806002]]></guid><cfi:id>975</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Identification of Aerodynamic Coefficients by Estimation-Before-Modeling Technique]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199806003]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[A nonlinear aerodynamic model has been identified by applying the estimation-before-modeling (EBM) technique to flight testing data. The two-part algorithm contains a nonlinear state estimator and a curve-fitting procedure. The results show that this technique is useful for quick determination of aerodynamic coefficients, and particularly applicable to nonlinear flight regimes, such as high angle-of-at tack regime.]]></description>
<pubDate>2014/1/3 16:01:52</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Xia Zhixun,Sheng Xiangrao and Tang Guojin]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Xia Zhixun,Sheng Xiangrao and Tang Guojin</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199806003]]></guid><cfi:id>974</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Whole Network Positioning of Small Satellite Constellation by Psecdocode Measuring Distance of GPS Carried on Satellite]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199806004]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In this paper, in order to improve the small satellite's positioning precision under constellation mode, we discuss a methed to deal with whole network datum of psecdocode measuring distance of GPS carried on the satellites, based on decreasing or eliminating error by difference between satellites and introducing the network restraint of constellation. After that, an actual example is given. Finally, we present several presumptions aiming at small satellite constellation's measurement and control, while not relying on GPS and raising the independence of small satellite constellation's positioning.]]></description>
<pubDate>2014/1/3 0:00:00</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Xi Xiaoning<sup>1</sup>,Zhang Yasheng<sup>1</sup>,Ren Xuan<sup>1</sup> and Zhu Wenyao<sup>2</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Xi Xiaoning<sup>1</sup>,Zhang Yasheng<sup>1</sup>,Ren Xuan<sup>1</sup> and Zhu Wenyao<sup>2</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199806004]]></guid><cfi:id>973</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Drop Size Correlation of Spray Models for RLPG]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199805001]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The atomization properties of annular injector in regenerative liquid propellant guns (RLPG) were experimentally investigated, by using the laser measurement of the temporal droplet size distribution of liquid spray. Empinical expression for mean droplet size of the annular injector spray was obtained. Some drop size correlation of spary models for RLPG was discussed. Valuable conclusions was presented.]]></description>
<pubDate>2014/1/3 16:01:37</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Wang Zhongwei,Zhou Jin,Zhong Liangsheng and Zhuang Fengchen]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Wang Zhongwei,Zhou Jin,Zhong Liangsheng and Zhuang Fengchen</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199805001]]></guid><cfi:id>972</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Transient Response Analysis of One Dimensional System by Distributed Transfer Function Method]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199805003]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The paper presents an analytical method for the analysis of dynamic response of one dimensional structures. In the analysis, the linear partial differential equations and the inhomogeneous boundary conditions that govern the response of the distributed subsystem are Laplace transformed with respect to time, and case into a state space form. The transfer function is determined in an exact and closed form by the state space technique. The transient response is obtained using the inverse Laplace transformation. Numerical examples are provided to illustrate the efficiency of the method.]]></description>
<pubDate>2014/1/3 0:00:00</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Feng Zhigang and Zhou Jianping]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Feng Zhigang and Zhou Jianping</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199805003]]></guid><cfi:id>971</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Recession Analysis of Carbon-Carbon Composite Nozzle of Liquid Propellant Rocket Engine]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199804001]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The recession process of C/C nozzle of liquid propellant rocket engine is studied. The analytical model consists of both solid-phase and gas-phase conservation equations. The gas-phase turbulent reactive flow of boundary layer is analyzed with the Favre-averaged equations to account for variable density effects. The unsteady heat conduction equation is used to obtain the temperature distribution of the nozzle wall with the numerical computation. The effects of mixture ratio, film cooling, chamber pressure and the density of the nozzle material on the recession rate are discussed.]]></description>
<pubDate>2014/1/3 16:01:26</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Liu Weiqiang and Chen Qizhi]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Liu Weiqiang and Chen Qizhi</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199804001]]></guid><cfi:id>970</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Verifying the Mathematical Model of State Characteristics of Liquid Rocket Engine by Using the Stochastic Simulation Method]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199804003]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[A pump-fed liquid rocket engine (LRE) is used as an object of study in this paper. By applying the stochastic simulation method, test data are used to verify the mathematical model of static characteristics of LRE. Not only are the actual measurement error range of the external interfering factors and the actual variation range of the internal interfering factors considered, but also the actual measurement error range of the engine parameters is considered during the model verification. The results of the model verification show that the mathematical model of static characteristics of LRE is accurate and the calculation methods employed are proper.]]></description>
<pubDate>2014/1/3 16:01:26</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Shen Chibing,Wu Jianjun,Wang Kechang and Chen Qizhi]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Shen Chibing,Wu Jianjun,Wang Kechang and Chen Qizhi</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199804003]]></guid><cfi:id>969</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[The Method of Source Terms Calculation in Grid Generation by Poisson Equations]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199804006]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Grid generation is very important to the numerical calculation of fluid flow. Many methods available can be used to achieve the target, but in this paper, only the method of Poisson equations was discussed. In addition to the traditional forms of source terms recommended by Thompson, a new one deduced by the authors was used in the calculation, and the comparison between the two forms gives several valuable conclusions.]]></description>
<pubDate>2014/1/3 16:01:26</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Yang Xiuting,Wang Zhenguo and Liu Weidong]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Yang Xiuting,Wang Zhenguo and Liu Weidong</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199804006]]></guid><cfi:id>968</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Analysis of the Dynamic Performance of a Parachute and Payload System]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199804007]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The three-dimension motion of a parachute and payload system is studied. Both the parachute and payload are assumed to have six degrees of freedom. They are coupled by a riser. The nonlinear differential equations of motion for a parachute-payload system are developed, which model the parachute suspension lines and the riser as inelastic elements. The resulting math model is then applied to analyze the dynamic performance of a drogue parachute recovery system. The simulation results are presented.]]></description>
<pubDate>2014/1/3 16:01:26</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Cheng Wenke,Yang Xiaowei,Qin Zizeng and Zhang Xiaojin]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Cheng Wenke,Yang Xiaowei,Qin Zizeng and Zhang Xiaojin</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199804007]]></guid><cfi:id>967</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[The Simulation and Test for Dynamic Response of the Electric Valves in Rocket Propulsion System]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199804010]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[According to the working principles of electric valves and sampling theorem, with the introduction of an equivalent circuit DXQ-1, the dynamic characteristics of electric valves in rocket propulsion system are simulated and the test technique is provided in this paper. The important circuit parameters are analyzed. Some theoretical results are also given.]]></description>
<pubDate>2014/1/3 16:01:27</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Zhang Junqing and Yang Leping]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Zhang Junqing and Yang Leping</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199804010]]></guid><cfi:id>966</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Analysis of the Test of Hot Fracture Toughness of Surface Cracks in the Welding Area of Aluminum Alloy]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199804011]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In this paper, a technique of testing the hot fracture toughness K<sub>Ie</sub> of surface cracks is recommended. With the help of the technique, the test sample is heated, the temperature is controlled and the (p-V) curve of the force p versus the open displacement V of a crack mouth is drawn automatically. The test accuracy is very high.]]></description>
<pubDate>2014/1/3 16:01:27</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Song Xiancun,Tang Guojin,Zhou Jianpin and Yuan Jiehong]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Song Xiancun,Tang Guojin,Zhou Jianpin and Yuan Jiehong</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199804011]]></guid><cfi:id>965</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[The Integrity Specification Techniques Based on the Grey Temporal Ordering Theory]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199804015]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The formal grey temporal security policy specification language (GTSL) which is designed by us is presented in this paper. The theory basis of GTSL is the theory of grey system and that of LOTOS, the language of temporal ordering specification. Due to the improvement and originality of techniques on the ability of integrity specification, the building and expression of the procedure of integrity verification, the testing of resonability on separation of duty, etc. , GTSL becomes practical specification languages for integrity security policy.]]></description>
<pubDate>2014/1/3 16:01:27</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Fan Aihua,Chen Huowang and Qi Zhichang]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Fan Aihua,Chen Huowang and Qi Zhichang</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199804015]]></guid><cfi:id>964</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Brief Introduction of Quantum Computation and Quantum Computer]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199804017]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In this paper, the history and development of quantum computation and quantum computer are reviewed. We explain that in what sense the quantum computer were shown to be more powerful than classical computer, introduce the network model and physics principle of the quantum computer and the difficulty in realization of the quantum computer.]]></description>
<pubDate>2014/1/3 16:01:27</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Li Chengzu,Zeng Chun and Huan Mingqiu]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Li Chengzu,Zeng Chun and Huan Mingqiu</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199804017]]></guid><cfi:id>963</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Development of Low Order Element with High Accuracy]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199804025]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In this paper problems which exist in 4-node isoparametric element and the methods of improving the accuracy are summerized. The authors give brief review to these methods and discuss the approach to developing high accuracy element.]]></description>
<pubDate>2014/1/3 16:01:28</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Ren Junguo and Xiong Longfei]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Ren Junguo and Xiong Longfei</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199804025]]></guid><cfi:id>962</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Analysis and Design of δ Constellation]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199803003]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The design of Satellite Constellation is one of the important steps to carry out space missions. This paper focuses mainly on the problem of how to design δ constellation effectively. The method, which is used to analyse the covering condition of some area with many satellites at one certain time, is discussed and certified. Based on this method, δ constellation is analysed by the means of simulating calculation. The method to design δ constellation is given at the end of the paper, and some δ constellation, which are designed by this method to fulfill some special needs, are listed.]]></description>
<pubDate>2014/1/3 0:00:00</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Chen Lei and Ren Xuan]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Chen Lei and Ren Xuan</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199803003]]></guid><cfi:id>961</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[The Study of DSMC Method in the High-altitude Plume Flowfield of Attitude-Control Thruster]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199803004]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In this paper, the character of high altitude plume flowfield is analyzed. The principle of DSMC method and its key points are also discussed. Then, the flowfield of nozzle exit vicinity and backflow region are calculated by using DSMC method, The results show that with this method, the flow property of this region can be accurately described.]]></description>
<pubDate>2014/1/3 16:01:16</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Huang Lin,Ren Bing and Wu Qifen]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Huang Lin,Ren Bing and Wu Qifen</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199803004]]></guid><cfi:id>960</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[The Numerical Simulation of Topological Structure in the Based Flow of Jet wake with Disturbance of a Main Flowfield]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199803005]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The numerical calculation of the unsteady full Navier-Stokes equations by means of time-marching is discussed in this thesis. To simulate jet wake and main flowfield's diturbance of axisymmetric blunt body, the finite volume method is used in the governing equations. The numerical results of time-marching give some fine topological structure of near wake. In addtion we make comparison and analysis in some different ratioes of pressure.]]></description>
<pubDate>2014/1/3 16:01:16</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Zheng Zhonghua,Chen Weifang and Wu Qifen]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Zheng Zhonghua,Chen Weifang and Wu Qifen</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199803005]]></guid><cfi:id>959</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Multigrid and TVD Scheme for Three Dimension Hypersonic Viscous Flowfield]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199802001]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In this paper, the time-dependent numerical method is used to solve the three dimensional Navier-Stokes equation. In the numerical procedure, Roe's flux difference splitting technique and Chakravarthy-Osher TVD scheme are used for the pressure and convective terms. Numerical solution of the Hypersonic laminer flow over a blunt biconic with 4°and 12°attack angle is obtained. The emphasis is placed on the predictions of the heat transfer rate on the wall. The numerical results of Stanton number are compared with the experimental data. And the multigrid method is also used to accelerate the convergence.]]></description>
<pubDate>2014/1/3 16:01:04</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Li Hua,Wang Chengyao and Wang Lei]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Li Hua,Wang Chengyao and Wang Lei</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199802001]]></guid><cfi:id>958</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Parallel Calculation of Implicit TVD Scheme for Hypersonic Flowfield]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199802002]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In this paper, the domain decomposition technique (DDT) and the parallel strategy of patched grid are used. The parallel numerical calculation on multiprocessors with TVD implicit finite volume algorithm is carried out for three dimensional hypersonic viscous flowfield by balancing load. The high speedup (the speedup is 1.84 on two processors and 3.44 on the four processors) has been obtained.]]></description>
<pubDate>2014/1/3 16:01:04</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Li Hua,Wang Chengyao,Wang Zhenghua and Wang Lei]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Li Hua,Wang Chengyao,Wang Zhenghua and Wang Lei</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199802002]]></guid><cfi:id>957</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[The Study of Characteristics of Resonators Used in Liquid Rockct Engines Combustion Stabilities Suppression]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199802004]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Helmholtz resonators and quarter-wave resonators are studied as the high-frequency combustion instabilities suppression devices in liquid rocket engines. Proper selection of the number of the resonators within the absorber arrangement is discussed. The damping characteristics of various length resonators are compared. Optimizing the system's damping by means of the absorption coefficient is suggested. The valuable results are proposed for designers.]]></description>
<pubDate>2014/1/3 16:01:05</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Nie Wansheng and Zhuang Fengchen]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Nie Wansheng and Zhuang Fengchen</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199802004]]></guid><cfi:id>956</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[A General Method for the Cycle Power Balance Calculation of the Liquid Rocket Engine]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199802006]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[A general method for the cycle power balance calculation of the liquid rocket engine is proposed in this paper. The components of the engine system are calculated iteratively in a predetermined sequence, and a modified Newton method is used to find the unknown variables of the system. This method is universal for the analysis of liquid rocket engine cycles. The program based on the method is achicved by the object-oriented programming. The stage combustion cycle using the liquid oxygen and methane as propellant is calculated with the program, and the calculation results are also given.]]></description>
<pubDate>2014/1/3 16:01:05</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Huang Weidong,Zhu Hengwei,Wang Kechang and Chen Qizhi]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Huang Weidong,Zhu Hengwei,Wang Kechang and Chen Qizhi</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199802006]]></guid><cfi:id>955</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[A Fault Detection Algorithm of Missle Based on Improved Kalman Filter]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199802007]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The drawbacks of the traditional Kalman filter arise from its requirement of accurate model and noise statistics which generally can' t be satisfied in engineering applications. An improved Kalman filter including inaccuracy in filter's initial condition is presented in this paper. By reducing the requirement of model accuracy, it can improves the robustness of Kalman filter under the model mismatch. Fault detection with this filter reduces the fault alarm rate owing to its stronger robustness. Because the accuracy of missile attitude control system model is limited, it is difficult to detect fault for the traditional Kalman filter owing to its weak robustness. The improved algorithm can detect faults effectively . A simulation example shows its validity.]]></description>
<pubDate>2014/1/3 16:01:05</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Wu Yaqing,Wu Jianjun and Su Mingzhao]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Wu Yaqing,Wu Jianjun and Su Mingzhao</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199802007]]></guid><cfi:id>954</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[An Accurately Integrated 4-Node Quadrilateral Element]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199801001]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In this paper，a new isoparametric transformation of a parallel quadrilateral parent element and the associated shape function is constructed to derive the accurately integerated stiffness matrix of the 4-nodes quadrilateral element. It has been demonstrated by theoretical and numerical analysis that the error of numerical integration is overcome by using the method and the computing speed of the method is almost three times of that of the two-point Gauss' integration.]]></description>
<pubDate>2014/1/3 16:00:52</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Yi  Xiaoshan,Ren Junguo and Zhou Jianping]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Yi  Xiaoshan,Ren Junguo and Zhou Jianping</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199801001]]></guid><cfi:id>953</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Numerical and Analytic Simulation of the Dynamic Stability Derivative of Blunt Cone]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199801002]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In this paper，the supersonic damping-in-pitch derivatives of blunt body are calculated with two methods. One is simulant unsteady viscous flow  field by solving N-S equations，and another is the analytic method of unsteady embeddy Newtonian theory. According to the numerical method，the  precision of unsteady flow calculation is improved by using sub-iteration. Similar results are abtained through the two methods. The numerical method can be applied to general flow calculation (3＜M<20,0°＜a＜20°).]]></description>
<pubDate>2014/1/3 16:00:52</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Liu Wei<sup>1</sup>,Shen Qing<sup>2</sup>,Zhang Lumin<sup>2</sup> and Zhang Hanxin<sup>2</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Liu Wei<sup>1</sup>,Shen Qing<sup>2</sup>,Zhang Lumin<sup>2</sup> and Zhang Hanxin<sup>2</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199801002]]></guid><cfi:id>952</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Study on Nonlinear High Frequency Acoustic Oscillation Combustion]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199801003]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The forming and developing processes of high frequency acoustic combustion are studied with the method of computational modeling in this paper.  The gas governing equations are described under the Euler coordinate，and the liquid phase governing equations are described under the Lagrangian coordinate. The high pressure combustion model is adopted. It is observed that the pressure oscillations near chamber head and  convergence is greater than others when there is high frequency combustion instability in the chamber. After comparing the pressure，the  temperature and velocity of the mixed gas under the condition of unstable combustion，the conclusion is drawn that the oscillation frequencies in two phase flow and combustor are the same when acoustic combustion occurs.]]></description>
<pubDate>2014/1/3 16:00:52</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Zhao Wentao<sup>1</sup>,Zhou Jin<sup>1</sup>,Nie Wansheng<sup>2</sup> and Zhuang Fengchen<sup>2</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Zhao Wentao<sup>1</sup>,Zhou Jin<sup>1</sup>,Nie Wansheng<sup>2</sup> and Zhuang Fengchen<sup>2</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199801003]]></guid><cfi:id>951</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[An Optimal Regression Approach to Fault Diagnosis of Liquid Rocket Engin]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199801004]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[An optimal regression approach to fault diagnosis of liquid rocket engine is presented in this paper，which can diagnose a number of faults with  fewer measurements. When the kinds of fault are fewer and the faults are not serious，rather satisfactory results of fault isolation and fault severity estimation are obtained. When the kinds of fault are fewer and the faults are serious，this approach still gives rather good fault   isolation result. When there exist several kinds of fault and the faults are serious，the diagnostic effect decreases somewhat. This indicates that the result of this method is satisfactory at a wide value range of fault factors.]]></description>
<pubDate>2014/1/3 16:00:52</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Zhu Hengwei,Huang Weidong,Wang Kechang and Chen Qizhi]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Zhu Hengwei,Huang Weidong,Wang Kechang and Chen Qizhi</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199801004]]></guid><cfi:id>950</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[The Bifurcated Stability Analysis of Rectangle Conical Shell under External Pressure]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199801005]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Applying 8-nodes degenerated element and non-linear finite element method，the stability of rectangle conical shell under external pressure has  been studied. Using the decrement method in the loading process，the curves of displacements and strains vs pressure have been obtained.  Numerical and experimental results show that while bifurcated unstability occurs，the displacements and strains would sharply change and this  can be used as a rule in the engineering analysis.]]></description>
<pubDate>2014/1/3 16:00:52</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Lin Xiqiang and Ren Junguo]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Lin Xiqiang and Ren Junguo</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199801005]]></guid><cfi:id>949</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[A Plate System with Uniform Suction in Low Speed Wind Tunnel]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199801006]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[A plate with uniform boundary layer suction is developed，on which the boundary layer can be controlled. The boundary layer velocity distribution on this plate is studied in various main flow velocities and suction coefficients. The experimental results are consistent with  the calculation's，and the experimental results of the high speed train models on this plate are also consistent with the foreign results of the  similar models on moving ground. The effect of the boundary layer can be eliminated effectively by using uniform suction plate，and thereby the  air forces of models can be measured more exactly.]]></description>
<pubDate>2014/1/3 16:00:53</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Yi Shihe,Chen Hong,Zou Jianjun and Wu Guifu]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Yi Shihe,Chen Hong,Zou Jianjun and Wu Guifu</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199801006]]></guid><cfi:id>948</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Distributed Transfer Function Method for Stability Analysis of Composite Conical Shells]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199906001]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In this paper, based on linear elastic and small deformation theory, an asymptotic distributed transfer function method (TFM) is presented for static deformation, free vibration and buckling analysis of isotropic/composite thin conical shells, where Fourier series expansion, Laplace transform, perturbation technique are applied. Synthesizing the transfer functions of sub-segments, the TFM solution is worked out for combined shells composed of several conical shell segments with different conical angle, thickness, complex boundary conditions and middle-supported constraints. Numerical results shows that this asymptotic TFM solution is of very high precision.]]></description>
<pubDate>2013/11/18 15:33:17</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Lei Yongjun,Li Haiyang and Zhou Jianping]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Lei Yongjun,Li Haiyang and Zhou Jianping</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199906001]]></guid><cfi:id>947</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Analysis Model of Composite Combined Beams by Distributed Parameter Transfer Function Method]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199906002]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In this paper, the distributed parameter transfer function method is applied to analyzing the vibration and stability of composite combined beams under axial compression. The Hamiltonian formalism of a modified mixed variational principle about the symptic variables is established using Legrendre transformation with spatial variable as independent variable instead of time. The state-space equations in Laplace transform domain is derived from using Hamilton's principle and Laplace transform. The unified and closed form transfer function solutions are obtained for vibration frequencies and buckling loads under arbitrary boundary restrictions. The influences of the first and high order shear deformation, torsion deformtion, rotary inertia, length-to-thickness ratio and material anisotropy on natural frequencies and buckling loads are investigated. Numerical examples are provided to demonstrate the efficiency and suitability of the methodology.]]></description>
<pubDate>2013/11/18 15:33:17</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Lei Yongjun,Li Haiyang and Zhou Jianping]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Lei Yongjun,Li Haiyang and Zhou Jianping</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199906002]]></guid><cfi:id>946</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Numerical Simulation of 3-D Chemical Non-equilibrium Flow over Reentry Capsule]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199906003]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The 3-D hypersonic chemical non-equilibrium flow over reentry capsule is simulated numerically. The full Navier-Stokes equations are taken as the governing equations. The chemical non-equilibrium air model is considered and seven species are N<sub>2</sub>、O<sub>2</sub>、NO、N、O、NO<sup>+</sup>、e<sup>-</sup>. Using NND Scheme for shock capture and implicit scheme to deal with the chemical source terms, the numerical results are in agreement compared with the experimental data. The perfect gas results are given for analysis of the real gas effect.]]></description>
<pubDate>2013/11/18 15:33:17</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Liu Jun,Zeng Ming and Qu Zhanghua]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Liu Jun,Zeng Ming and Qu Zhanghua</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199906003]]></guid><cfi:id>945</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Decoupling Design for Bank-to-turn Missile Autopilot Using Multivariable Frequency-domain Approach]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199906004]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In this paper the method of a bank-to-turn missile autopilot design is studied. The unsquared yaw-roll channel model with serious coupling is squared by first using inner closed-loop method firstly. Then the autopilot is designed using the multivariable frequency-domain approach based on the Nyquist array method. The simulation shows the efficient decoupling.]]></description>
<pubDate>2013/11/18 15:33:17</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Guo Hongwu and Liu Mingjun]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Guo Hongwu and Liu Mingjun</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199906004]]></guid><cfi:id>944</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Numerical Simulation of Blast Interaction with the Forest Fires]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199906005]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The paper discusses the basic principles of extinquishing the forest fires by blast and its feasible research direction. As the first step, flows of blast waves near the earth are simulated numerically by use a new ENO scheme which was simple structure and efficient to use.]]></description>
<pubDate>2013/11/18 15:33:17</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Liu Jun,Zhou Yongwei and Chang Xiyu]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Liu Jun,Zhou Yongwei and Chang Xiyu</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199906005]]></guid><cfi:id>943</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Numerical Computations of Trans-sonic Dispenser Cavity Flow]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199906009]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The combination of SLIP scheme and LU-SSOR method is used to predict the steady-state aerodynamics of trans-sonic ogive dispenser at Mach number 0.94 to 0.98; and the modified B-L turbulence model is applied in solving axisymmetric Navier-Stokes equation. Computed surface pressures of dispenser without cave have been compared with experiments as well as Sahu's numerical results and are found to be in good agreement; The results of cavity flow are also found to be reasonable.]]></description>
<pubDate>2013/11/18 15:33:17</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Xia Gang<sup>1</sup>,Wang Chengyao<sup>1</sup> and Yang Xiaohui<sup>2</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Xia Gang<sup>1</sup>,Wang Chengyao<sup>1</sup> and Yang Xiaohui<sup>2</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199906009]]></guid><cfi:id>942</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[The Flowrate Characteristics of Gas-liquid Coaxial Swirling and Unswirling Injectors]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199905001]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[This paper presents the result of an experimental study on the flowrate characteristics of coaxial swirling injector and coaxial unswirling injector. Effects of the interaction between gas and liquid flows in injector and the change of environmental pressure on the flowrate characteristics of injectors are investigated. The results show that the effect of the interaction between gas and liquid flows is much more significant for coaxial swirling injector than that for coaxial unswirling injector, and that increasing environmental pressure results in the same effects on the gas flowrate characteristics, but effects on the liquid flowrate characteristics for these two type injectors are different.]]></description>
<pubDate>2013/11/18 15:32:31</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Zhou Jin,Tong Rongyu,Shen Chibing,Li Qinwu and Wang Zhenguo]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Zhou Jin,Tong Rongyu,Shen Chibing,Li Qinwu and Wang Zhenguo</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199905001]]></guid><cfi:id>941</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Generalized Super-Element based on Strip Distributed Transfer Function Method]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199905002]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Based on the theory of strip distributed transfer function method (SDTFM), a new element, called generalized super-element (GSE) is given for 2-D problems and its stiffness matrix and nodal force vector are derived. With the use of generalized super-element, the application of SDTFM is extended to the 2-D problems of arbitary geometrical boundary.]]></description>
<pubDate>2013/11/18 15:32:31</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Huang Zhuangfei and Zhou Jianping]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Huang Zhuangfei and Zhou Jianping</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199905002]]></guid><cfi:id>940</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[A Model for Attacking Mobile Missile's Sector Base and its Realization]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199905003]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Attacking the mobile missile base is considered and an aiming-point-choosing model for striking its sector mobile region is presented. The model is realized and the result is analyzed. The model has generality for attacking mobile target and is also useful for making an operational decision.]]></description>
<pubDate>2013/11/18 15:32:31</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Bi Yiming,Wu Faping and Li JingWen]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Bi Yiming,Wu Faping and Li JingWen</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199905003]]></guid><cfi:id>939</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Distributed SPP Algorithm for Tridiagonal Equations]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199905004]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[SPP algorithm is developed for the solution of tridiagonal and block tridiagonal equations. In the solution of the tridiagonal system, file I/O and result transfers are time consuming. SPP algorithm has taken the characteristic into account. The overlapping of computation, file I/O and communication is fully exploited. The computation count and communication count are analysed. The algorithm is tested on NOWs. It shows that SPP algorithm is suitable for distributed computing.]]></description>
<pubDate>2013/11/18 15:32:31</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Wang Zhenghua,Che Yonggang and Zhao Wentao]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Wang Zhenghua,Che Yonggang and Zhao Wentao</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199905004]]></guid><cfi:id>938</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[A Parallel Algorithm for the Fusion Method for Estimate of Trejectory]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199905005]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The number of operations of the algorithm for measurement element selection is very large. The paper deals with this question. And its parallel algorithm is presented, with regard to the fusion method in reference [1]. The scalability for the algorithm is analyzed. The predicted speed-ups are given.]]></description>
<pubDate>2013/11/18 15:32:31</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Tong Li,Zeng Yonghong and Zhu Jubo]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Tong Li,Zeng Yonghong and Zhu Jubo</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199905005]]></guid><cfi:id>937</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[The General Expression for the Lateral Vibration Frequency Equations of Compressed Bars on Elastic Foundations]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199905012]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The general expression for the lateral vibration frequency equations of compressed straight bars with constant cross section on elastic foundations is deduced in this paper. Each particular case under the conditions at the end of the bar is analysed and discussed.]]></description>
<pubDate>2013/11/18 15:32:31</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Huang Yan]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Huang Yan</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199905012]]></guid><cfi:id>936</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[The General Trajectory Simulation Model Considering Mass Center's Flow and Bias]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199905013]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The concept of mass center coordinate system is introduced. The definition of missile coordinate system is modified. The general trajectory simulation model with mass center's flow and bias under consideration is presented and the respective formulas for moment of inertia and product of inertia are given.]]></description>
<pubDate>2013/11/18 15:32:31</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Sun Pizhong,Tang Guojin and Xia Zhixun]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Sun Pizhong,Tang Guojin and Xia Zhixun</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199905013]]></guid><cfi:id>935</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[An Investigation of Difference Schemes for Numerical Simulation of Hypersonic Viscous Flowfield]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199904001]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In this paper, the time-dependent numerical method has been used to solve the three dimensional Navier-Stokes equation, the numerical procedure uses Roe's flux difference splitting technigue and TVD scheme or LED scheme for the convective terms and central differencing scheme for viscous terms. Numerical solution of hypersonic laminar flow over a blunt biconic with attack angle is obtained.The resolution of shock, computational accuracy of viscous boundary layer and the efficiency of three schemes: Osher-Chakraverthy's TVD scheme, Harten's TVD scheme and Jameson's LED scheme, are investigated and compared by the numerical calculation of three dimensional hypersonic viscous flow.]]></description>
<pubDate>2013/11/18 15:32:45</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Li Hua,Wang Lei and Wang Chengyao]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Li Hua,Wang Lei and Wang Chengyao</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199904001]]></guid><cfi:id>934</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Study of Flow's Similitude Law]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199904002]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Being different from classic dimension analysis method and dimensionless method of flow's governing equations and its certain resolving conditions, this paper presents a new method to analyze flow's similitude law, scilicet decomposing complicated flow process to some sub-processes and analyzing characteristic quantity which represents sub-process' essence nature. According to this new method this paper presents law of similitude in non-equilibrium thermo-chemistry hypersonic flows, which is consistent with the law of similitude obtained by classic method in reference.]]></description>
<pubDate>2013/11/18 15:32:45</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Chen Weifang,Shi Yuzhong,Cao Dengtai and Wu Qifeng]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Chen Weifang,Shi Yuzhong,Cao Dengtai and Wu Qifeng</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199904002]]></guid><cfi:id>933</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Three Dimensional Numerical Simulation in Liquid Rocket Engine with the Method of Parallel Processing Technique]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199904003]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The complex three dimensional flow field in liquid rocket engine is simulated with the method of predictive and corrective MacCormack scheme, and the parallel computation is carried out under the PVM circumstance which is made up of network of microcomputer. The results show that parallel and distributed method can play an important role on the numerical simulation in liquid rocket engine.]]></description>
<pubDate>2013/11/18 15:32:45</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Zhao Wentao,Wang Zhenghua,Liu Zhong and Yang Xiaodong]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Zhao Wentao,Wang Zhenghua,Liu Zhong and Yang Xiaodong</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199904003]]></guid><cfi:id>932</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Experimental Investigation on Mixing Characteristics of Tripropellant Injectors]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199904004]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Four types of GH<sub>2</sub>/LO<sub>2</sub>/RP-1 tripropellant injectors are employed to present the mixing characteristics test in this paper. The effects of the internal injector's recess on the mixing characteristics of the swirl coaxial injector with separate fuel injection are studied. The mixing characteristics of each injector are compared with those of the others in the same tripropellant operating condition. The effects of the injectors' configuration on the mixing characteristics are analyzed. The mixing characteristics tests of the single injector and three injectors are presented. The tests results show that the span of the mass flux distribution of the shear coaxial injector is smaller than that of the swirl coaxial injector in the same tripropellant operating condition. The conclusions reached in this paper provide a reference for the optimization design of the tripropellant injectors and the gas/liquid coaxial injectors.]]></description>
<pubDate>2013/11/18 15:32:45</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Shen Chibing,Jiang Chunlin,Tong Rongyu,Zhou Jin and Wang Zhenguo]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Shen Chibing,Jiang Chunlin,Tong Rongyu,Zhou Jin and Wang Zhenguo</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199904004]]></guid><cfi:id>931</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Bayesian Evaluation of Maximum Distance Considering Credibility]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199904005]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[First, a new method of consistent testing in prior data and testing data is discussed. Considering credibility, we study Bayesian inference and Bayesian of maximum distance. Finally, the example is given.]]></description>
<pubDate>2013/11/18 0:00:00</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Zhang Shifeng and Gong Erling]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Zhang Shifeng and Gong Erling</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199904005]]></guid><cfi:id>930</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Numerical Distributed Transfer Function Method for Wedge Beam]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199904006]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[A numerical distributed transfer function method (NDTFM) is introduced for the analysis of state space equations of distributed parameter systems with variable coefficients. The method is the extension of DTFM (distributed transfer function method), and it is easy to use for various physical-mathematical problems with variable parameters. Wedge beam is analyzed using this method, and a general element is derived to raise numerical efficiency. Numerical results show that this method is efficient and easy to use.]]></description>
<pubDate>2013/11/18 15:32:46</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Li Haiyang,Zhou Jianping and Feng Zhigang]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Li Haiyang,Zhou Jianping and Feng Zhigang</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199904006]]></guid><cfi:id>929</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Optimal Controlling of Electrorheological sandwich beam]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199904007]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Electrorheological (ER) materials experience real-time and reversible changes in rheological and mechanical properties when subjected to electrical fields, which draw much attention to the use of ER materials in adaptive structures recently. ER sandwich beam is composed of two elastic layers and sandwiched ER layer. By controlling the pre-yield rheological and mechanical properties of ER materials, the dynamical response of the composed beam is then controlled. In this paper, ER sandwich beam simply supported at two ends is moded. The dynamical response of ER sandwich beam and the optimal electrical fields corresponding to different frequency are analyzed.]]></description>
<pubDate>2013/11/18 15:32:46</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Li Daokui<sup>1</sup>,Zhang Zhongli<sup>1</sup> and Yang Guangsong<sup>2</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Li Daokui<sup>1</sup>,Zhang Zhongli<sup>1</sup> and Yang Guangsong<sup>2</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199904007]]></guid><cfi:id>928</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Numerical Solution of Symmetric Thermochemical Nonequilibrium Flowfield over FIREII Capsule]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199903001]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The symmetric thermochemical nonequilibrium flow is simulated numerically. The full Navier-Stokes equations are taken as the governing equations. The time-dependent analysis is used. The two-temperature and seven species gas model is adopted. NND scheme for shock capture and time preconditional metrix technique are used for numerical solution. The influence of thermochemical nonequilibrium on flow field is analysed.]]></description>
<pubDate>2013/11/18 15:33:02</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Huang Hua,Liu Jun and Qu Zhanghua]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Huang Hua,Liu Jun and Qu Zhanghua</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199903001]]></guid><cfi:id>927</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[The Application of Singular Integral Equation to the Dynamic Fracture Analysis of Cracked Strip (I)]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199903003]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[By using the integral transform method, the problem of an infinitely long elastic strip with a Griffith crack is converted into a Cauchy-type singular integral equation in Laplace transform domain. By solving the singular integral quation and analyzing the asymptotic behavior of the crack tip field, the dynamic stress intensity factor in Laplace transform domain is gotten.]]></description>
<pubDate>2013/11/18 15:33:02</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Yuan Jiehong,Tang Guojin and Zhou Jianping]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Yuan Jiehong,Tang Guojin and Zhou Jianping</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199903003]]></guid><cfi:id>926</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[The Application of Singular Integral Equation to the Dynamic Fracture Analysis of Cracked Strip (II)]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199903004]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[By using Durbin's inverse Laplace transform method, the dynamic stress intensity factor in Laplace transform domain is transformed into the result in time domain. The numerical example is given and the reasonability of the method in this paper is verified. By analyzing the calculating result, some interesting and significative conclusions are presented.]]></description>
<pubDate>2013/11/18 15:33:02</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Yuan Jiehong,Tang Guojin and Zhou Jianping]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Yuan Jiehong,Tang Guojin and Zhou Jianping</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199903004]]></guid><cfi:id>925</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Numerical Solution of Viscous Shock Layer Flow of 11-Species Chemical Reacting Air over Blunt Bodies]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199903005]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In this paper, 11-species Air Model is used for calculating the chemical non-equilibrium viscous shock layer flow over hyperboloids. The stagnation streamline distributions of pressure、temperature and N<sup>+</sup><sub>2</sub>、O<sup>+</sup><sub>2</sub>、N<sup>+</sup>、O<sup>+</sup>、NO<sup>+</sup> and e<sup>-</sup> number density are given and compared with the results of 7-species、5-species models.]]></description>
<pubDate>2013/11/18 15:33:02</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Zhang Qiaoyun and Qu Zhanghua]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Zhang Qiaoyun and Qu Zhanghua</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199903005]]></guid><cfi:id>924</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[The Calculation of Aerodynamics and Flare Control Force for Controlled Parafoil]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199903006]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In this paper, the“equivalent airfoil flexible model”for the aerodynamic calculation and the“two body hinged model”for the flare control force calculation of a parafoil is established. The aerodynamics of the parafoil is calculated by using the nonplane-vortex-grid-method. On the basis of these calculation results, the flare control force is calculated.]]></description>
<pubDate>2013/11/18 15:33:03</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Zhang Shunyu,Qin Zizeng and Zhang Xiaojin]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Zhang Shunyu,Qin Zizeng and Zhang Xiaojin</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199903006]]></guid><cfi:id>923</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Analytic Solution of Global Path Planning for Space Free-flying Robotics]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199903007]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[One of the most important problems in space based robotics is the disturbance to the satellite attitude caused by satellite mounted manipulators operation. In this paper the dynamic equations and conservation of angular momentum of a space manipulator system which are considered subject conditions are developed by using the“Virtual Manipulator Mode”;According to skew Matrix about skew motion of rigid body, we put out with a function to comment on the attitude change of rigid body; the we present a technique called“periods motion“to find an globally optimal path planning in form of analytic function solution.]]></description>
<pubDate>2013/11/18 15:33:03</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Zhang Qingbin,Tang Qiangang and Sun Shixian]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Zhang Qingbin,Tang Qiangang and Sun Shixian</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199903007]]></guid><cfi:id>922</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[The Orbit Models for Designing LEO Satellite Constellations]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199902001]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[the orbit models, the calculation methods of sub-satellite and the coverage judgement which take into account the J<sub>2</sub> perturbations are given first, and then an iterating methods of designing satellite orbit with repeat ground trace is proposed. The near-circle low earth orbits which repeat after 12、13、14、15 orbits per day are often chosen in designing regional partial coverage constellations, so the heights and the inclination angles of these 4 kinds orbits are listed in the end.]]></description>
<pubDate>2013/11/18 15:33:33</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Bai Hefeng,Ren Xuan and Xi Xiaoning]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Bai Hefeng,Ren Xuan and Xi Xiaoning</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199902001]]></guid><cfi:id>921</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[The Research of Efficient Method for Computing Basic Firing Data of Ballistic Missiles]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199902002]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[This paper applies Newton iterative method to computing basic firing data of ballistic missiles efficiently. In this paper, Newton iterative formula based on deviations of dropping point is deduced and the iterative program is designed, an example is given. Considering the relationship between the convergent speed of the iterative method and the initial value of parameters, the paper brings forward a method, which provides good initial values of parameters by using a reverse interpolation method based on prepared firing tables. The actual practice indicates that the method accelerates iteration rapidly. It is possible to design a standard trajectory of ballistic missiles quickly by using the method presented in this paper.]]></description>
<pubDate>2013/11/18 15:33:33</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Wang Haili,Chen Lei and Hu Xiaoping]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Wang Haili,Chen Lei and Hu Xiaoping</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199902002]]></guid><cfi:id>920</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Application of MESA on Validating Missile Simulation Model]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199902003]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The quantitative method of missile simulation model validation is discussed. According to the characteristic of high accuracy of MESA, the approximate statistical property is analyzed, the consistence tests of two samples and of two normal ensembles are given respectively. It's proved by simulation that validation by MESA is feasible. An applicable example is given, to validate simulation model of homing guidance missile by MESA.]]></description>
<pubDate>2013/11/18 15:33:33</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Li Pengbo and Gao Xia]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Li Pengbo and Gao Xia</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199902003]]></guid><cfi:id>919</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Thermal Analysis of GO<sub>2</sub>/Kerosene Rocket Thrust Chamber Wall]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199902004]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Unsteady three-dimensional thermal analysis model of the chamber wall is used to account for the thermal protection of GO<sub>2</sub>/kerosene ground test engine and numerical calculation is performed on its water cooling channel wall. The numerical model treats the hot gas flow and coolant flow as one dimensional. The hot gas side heat transfer and the temperature profile in the wall are obtained by finite difference method. The history of the temperature profile is also predicted by the analysis. The effect of the coolant flow rate on the temperature profile is also discussed.]]></description>
<pubDate>2013/11/18 15:33:33</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Liu Weiqiang,Jiang Chunlin,Zhou Jin,Wang Zhenguo and Chen Qizhi]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Liu Weiqiang,Jiang Chunlin,Zhou Jin,Wang Zhenguo and Chen Qizhi</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199902004]]></guid><cfi:id>918</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[The Asymptotic Method for One Dimensional Non-uniform Distributed Parameter Systems by Distributed Transfer Function Mcthod]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199902005]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Non-uniform beam-like structures have been widely used in engineering structures to achieve an optimal distribution of strength, stiffness and modes of vibration to satisfy design requirements. In this paper, a new asymptotic method for the analysis of these systems is presented. The linear partial differential equation which governs the response of the beam and the inhomogeneous boundary conditions have been put into a state space form. Choosing the small parameterεas a perturbation parameter, the asymptotic solutions are determined by the state space technique. Numerical examples are provided to illustrate the efficiency of the method.]]></description>
<pubDate>2013/11/18 0:00:00</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Feng Zhigang,Zhou Jianping and Li Haiyang]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Feng Zhigang,Zhou Jianping and Li Haiyang</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199902005]]></guid><cfi:id>917</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Application of Grid-Embedding Technique to 2-D Unsteady Inviscid Flowfield]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199902006]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[A two-dimensional TVD scheme with second order accuracy in space and time is used to simulate the horizontal relative motion flowfield between wedges. Grid-embedding technique is applied to calculate the unsteady flowfield. This technique simplifies the construction of computational grids about complex geometries and allows relative motion between embedded grids.]]></description>
<pubDate>2013/11/18 15:33:33</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Kong Jinzhu and Wang Chengyao]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Kong Jinzhu and Wang Chengyao</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199902006]]></guid><cfi:id>916</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Vibration Control Of Beam Containing Piezoelectric Patches]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199902007]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[By applying heaviside function, the vibration equation governing the beam that possesses spatially distributed piezoelectric patches has been established. Based on this equation and using the modal method, some problems about the vibration control have been discussed. Numerical examples have been presented to illustrate the efficacy of the control to both free and forced vibration.]]></description>
<pubDate>2013/11/18 15:33:33</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Lin Xiqiang and Ren Junguo]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Lin Xiqiang and Ren Junguo</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199902007]]></guid><cfi:id>915</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Study on the Directional Scatter of Warhead Fragments]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199902008]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In this paper, we research on spatial scatter of preformed fragmentary steel shell under detonation driving. Four different explosive charges are considered. In order to abtain a parallel fragment spatial scattering pattern, there are special requirements on the geometry of the shell and the initial velocities of the fragments. These requirements have been discussed in detail in the paper.]]></description>
<pubDate>2013/11/18 15:33:33</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Wang Chenhong,Zhang Ruoqi,Zeng Xinwu and Jiang Houman]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Wang Chenhong,Zhang Ruoqi,Zeng Xinwu and Jiang Houman</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199902008]]></guid><cfi:id>914</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[The Vehicle's Departure Velocty Measurement System]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199902009]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The paper introduces a new type of velocity measurement system. In this system, the displacement can he changed into electronic signals with reflective stripe optoelectronic technology for the first time, the data are collected by writing the computer's memory directly and timely. The measurement results can be printed immediately. The system can provide highly accurate measurement and is easy to operate. It can be used widely.]]></description>
<pubDate>2013/11/18 15:33:33</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Song Xiancun,Zhou Jianping,Shan Xiaoqiang,Liu Daquan and Zhang Hailian]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Song Xiancun,Zhou Jianping,Shan Xiaoqiang,Liu Daquan and Zhang Hailian</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199902009]]></guid><cfi:id>913</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[On chemical Non-equilibrium VSL Fow over a Teflon Ablative Wall]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199901001]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The chemical non-equilibrium viscous shock layer flows over a teflon ablative wall are calculated numerically. The coupled solutions of the chemical non-equilibrium viscous shock layer flows and the teflon ablative procedures are obtained through space-marching and global iterations. The overall teflon-air chemical system used consists of 19 species and 29 reactions. The effects of the equilibrium catalytic and the noncatalytic wall conditions on the ablative flows are discussed.]]></description>
<pubDate>2013/11/15 15:37:24</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Shi Yuzhong,Zheng zhonghua and Wu Qifen]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Shi Yuzhong,Zheng zhonghua and Wu Qifen</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199901001]]></guid><cfi:id>912</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Methods for Solving Boltzmann Equation]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199901002]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Various methods for solving Boltzmann equation are discussed in this paper. After analyzing the advantagesit and shortcomings of each method, it is shown that at present the direct simulation Monte-Carlo method is the best approach to solving rarefied gas dynamic problems.]]></description>
<pubDate>2013/11/15 15:37:24</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Chen Weifang and Wu Qifen]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Chen Weifang and Wu Qifen</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199901002]]></guid><cfi:id>911</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Investigation on Mechanical Properties for Three-dimensional Braided Circular Tubes and the Bearing Capacities for the Analogue Structure of a Rocket Linking-Stage]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199901003]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The compression and torsion behavior for the three-dimensional braided C/E 4-D and 5-D circular tubes and the axial compression bearing-capacity for the Analogue Structure of Rocket Link-stage were investigated by experimental method in this paper. The experimental results show that the compression behavior for 5-D material is superior to 4-D material but the shear modulus for 5-D specimens are nearly the same with 4-D ones. The 3-cell model and FGM model are applied to predict the relative properties and compression strength of the tubes. The comparisons between the theoretical results and the experimental ones indicate that the predict results by 3-cell model are fairly coincident with the experiments, and the predict values by FGM model are lower. The results in this paper are a good basis for the designer of the braid sructures.]]></description>
<pubDate>2013/11/15 15:37:24</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Shen Huairong<sup>1</sup> and Zheng Wenglong<sup>2</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Shen Huairong<sup>1</sup> and Zheng Wenglong<sup>2</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199901003]]></guid><cfi:id>910</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[The Architecture of the Simulation-Based Evaluation System for Missile Effectiveness]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199901005]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The acquisition of missile system MOE (measure of effectiveness) depends on its corresponding model/simulation supporting system. The simulation based missile combat effectiveness evaluation system has complex structure. Architecture theory is a useful technique to deal with the system structural complexity problem. This paper proposes an architecture for missile effectiveness evaluation system based on software architecture theory.]]></description>
<pubDate>2013/11/15 15:37:24</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Yang Feng,Zhang Xuebin,Wang Weiping and Sha Jichang]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Yang Feng,Zhang Xuebin,Wang Weiping and Sha Jichang</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199901005]]></guid><cfi:id>909</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Methodology for Simulation of Missile System Combat Effectiveness Evaluation]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199901006]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[This paper deals with the four critical areas in the evaluation of the missile combat effectiveness based on engagement simulation. A common procedure for this method is presented, which can be used for the application of engagement simulation to the evaluation of the combat effectiveness of all kinds of missile systems.]]></description>
<pubDate>2013/11/15 15:37:24</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Chen Jingliang,Zhu Yifan,Zhang Xuebin and Wang Weiping]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Chen Jingliang,Zhu Yifan,Zhang Xuebin and Wang Weiping</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199901006]]></guid><cfi:id>908</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Simulation Model for Tactical Ballistic Missile Engagement in Electrical Combat Case]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199901007]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[This paper presents an object-oriented simulation model for TBM engagement in electrical combat, proposes the structure of this model with the characteristics of simulation on TBM engagement, and discusses the corresponding simulation algorithm.]]></description>
<pubDate>2013/11/15 15:37:24</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Zhu Yifan,Zhang Xuebin,Wang Weiping and Yang Feng]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Zhu Yifan,Zhang Xuebin,Wang Weiping and Yang Feng</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199901007]]></guid><cfi:id>907</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Analytical Model on Intercepting Decision of Anti-Tactical Ballistic Missile]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199901008]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The Anti-Tactical Ballistic Missile (ATBM) plays a more and more important role in the air defense system, and the intercepting decision is a main step in the intercepting process. In this paper, considering the case of large numbers of offensive objects and the constraint of the interceptive ability of the ATBM, the authors provide a general optimized decision model, using 0-1 integral schedule method, to determine the best intercepting plan.]]></description>
<pubDate>2013/11/15 15:37:24</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Zhu Yifan,Zhang Xuebin,Wang Weiping and YangFeng]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Zhu Yifan,Zhang Xuebin,Wang Weiping and YangFeng</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199901008]]></guid><cfi:id>906</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Simulation Model for Radar Net of Patriot Missile]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199901009]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[This paper studies the detection characteristics of radar net in“Patriot”missile system. After discussing the detection principle of the radar net and its stationing mode (balanced and weighed), the authors propose the distributed target detection model of radar net in“Patriot”missile system.]]></description>
<pubDate>2013/11/15 15:37:24</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Xiao Shunping,Wang Guoyu and Ma Jianwu]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Xiao Shunping,Wang Guoyu and Ma Jianwu</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/199901009]]></guid><cfi:id>905</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Motion Analysis and Orbit Design of Formation Flying Satellites Based on Hill-Equation]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200006001]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In this paper, based on the Hill-equation, the property of the flying-around orbit and the orbit design method of formation flying satellites are studied. The flying-around orbit is described in three respects: the coordinate-plane projection, the angle with the coordinate-plane, flying-around orbit elements. The orbit design of formation flying satellites is done in two steps: first the basic surrounding satellite, then the other surrounding satellites. Numerical results show that this method is suitable for the preliminary design of formation flying.]]></description>
<pubDate>2013/11/18 15:31:15</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[ZHANG Yukun,DAI Jinhai,WANG Shi and REN Xun]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>ZHANG Yukun,DAI Jinhai,WANG Shi and REN Xun</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200006001]]></guid><cfi:id>904</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Finite Element Model for the Joints in Multi-body Structures]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200006002]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[A finite element model for the joints in multi-body structures has been presented. Based on the mechanical principles, the stiffness matrix and damping matrix of the finite element of the joint have been deduced. By this way, the non-continuous physical system becomes continuous mathematically. So, the idea presented in this paper gives us another way to analyze the dynamical problem in a multi-body structures.]]></description>
<pubDate>2013/11/18 15:31:15</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LI Dongxu,SUN Peizhong and TANG Qiangang]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LI Dongxu,SUN Peizhong and TANG Qiangang</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200006002]]></guid><cfi:id>903</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Research on the Mechanic-Electric Property of a Piezoelectric Control Film]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200006003]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The mechanic-electric properties of a piezoelectric film have been analyzed. The piezoelectric strain equation has been deduced, too. The research results have shown the working principle of the piezoelectric film in smart structures.]]></description>
<pubDate>2013/11/18 15:31:15</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LI Dongxu and GUAN Yuqiu]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LI Dongxu and GUAN Yuqiu</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200006003]]></guid><cfi:id>902</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[The Wind Compensation of Ballistic Trace of a Low Altitude Sounding Rocket with the Translation Model from Variable Wind to Constant Wind]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200006004]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[An automatically iterative method to get optimal wind compensation launching configurations of the sounding rocket is proposed. The method avoids error of applying approximative theory and accelerates convergence by using adapt-step search. In addition, a new method to translate from variable wind to constant wind is also presented. The variable wind and result constant wind are equal in effect on trace of rocket.The more satisfactory results by two methods are shown.]]></description>
<pubDate>2013/11/18 15:31:15</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[MA Min,ZHANG Dongsheng,ZHANG Weihua and GAN Chuxiong]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>MA Min,ZHANG Dongsheng,ZHANG Weihua and GAN Chuxiong</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200006004]]></guid><cfi:id>901</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Buckling Analysis of Delaminated Shell for the First Order Shear Deformation Theory]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200005001]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Delaminations may greatly reduce the buckling load of the laminated structure. Cylinder including arbitrary delaminations in longitudinal and thickness and spaning the entire circumference was divided into multiple sublaminates shell whose longitude displacements were simulated with linear function of the thickness coordinate. The variational principle was applied to obtain the governing equations and boundary conditions. The state-space scheme was used to solve the problem. By comparing with classical theory, the usable range of each theory was pointed out. Three difference buckling modes of delaminated shell were considered. The influence of boundary condition, length and depth of delamination on buckling load was analyzed. Finally, the buckling analysis of delaminlated orthotropic shell was given.]]></description>
<pubDate>2013/11/18 15:30:32</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LI Daokui,ZHOU Jianping and LEI Yongjun]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LI Daokui,ZHOU Jianping and LEI Yongjun</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200005001]]></guid><cfi:id>900</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[The Analysis of Large Deformation of Pure Bending in Beams]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200005002]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In the plane stress problem, the exact solution of stress in pure bending of beam acted by linear distributed external forces is obtained. The approximate solution of displacement is obtained by Euler method. When Poisson's ratio is zero, the exact solution of displacement is obtained.]]></description>
<pubDate>2013/11/18 15:30:32</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[ZHANG Xiaojin and HUANG Yan]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>ZHANG Xiaojin and HUANG Yan</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200005002]]></guid><cfi:id>899</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Numerical Simulation of Hypersonic Viscous Flows Over Liftbody-Type Vehicle]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200005003]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Using alternating direction implicit NND scheme, the TLNS equations were solved under the assumption of perfect gas, and the space grids of complex wing-shape were generated by solving parabolic partial differential equations. Finally, the numerical simulation results of liftbody-type were shown under the conditions: M<sub>∞</sub>=8.0,α=20°.]]></description>
<pubDate>2013/11/18 15:30:32</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LIU Wei and LIU Jun]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LIU Wei and LIU Jun</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200005003]]></guid><cfi:id>898</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Numerical Simulation of Plug Nozzle in Supersonic Flow]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200005004]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Interaction of plug nozzle jets with supersonic external flow was simulated numerically based on 3-D TLA NS equations with ENO scheme, then the structure of the flow field was analyzed. Calculations were performed under two-component model in which the external flow was air and the jet was fuel gas. Turbulence was taken into account with a k-ε turbulence model. The results agreed well with the reference.]]></description>
<pubDate>2013/11/18 15:30:32</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LIU Jun and GUO Zheng]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LIU Jun and GUO Zheng</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200005004]]></guid><cfi:id>897</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[A New Uncoupled Method for Numerical Simulation of Nonequilibrium flow]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200005005]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[An new uncoupled method was introduced to simulate numerically nonequilibrium flow which had the stiffness problem. The flow phenomenon of H<sub>2</sub>/O<sub>2</sub> combustion induced by shock was simulated with the method, based on N-S equations and NND2M scheme. The results indicated that the method was simple and efficient in the application to multi-component and multi-reaction flow.]]></description>
<pubDate>2013/11/18 15:30:32</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LIU Jun<sup>1</sup>,ZHANG Hanxin<sup>2</sup> and GAO Shuchun<sup>2</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LIU Jun<sup>1</sup>,ZHANG Hanxin<sup>2</sup> and GAO Shuchun<sup>2</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200005005]]></guid><cfi:id>896</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Test Research on the Ignition Characteristics of Minute Solid Rocket Motor]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200005006]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[A kind of igniter has been designed for minute solid rocket motor. Many tests have been done to determine the ignition characteristics of minute solid rocket motor. A concept of initial ignition pressure has been introduced the principal principle which effected ignition delay time scatter has been found and determined the ignition scheme satisfying the demand for ignition performance of minute solid rocket motor determined.]]></description>
<pubDate>2013/11/18 15:30:32</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[SUN Pizhong,QIN Zizeng,ZHANG Xiaojin and GUO Jian]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>SUN Pizhong,QIN Zizeng,ZHANG Xiaojin and GUO Jian</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200005006]]></guid><cfi:id>895</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Preliminary Study of Asymmetric Nozzle of Free-vortex Aerodynamic Window]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200005007]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The crystal window of high-power laser can not work in gear because of the heat caused by absorption of high-power beam. The supersonic free-vortex segment is usually employed to seal low-pressure laser-cavity. In this article the procedures are described for determining free-vortex segment properties. Characteristics method is used to design nozzle which produces free-vortex segment.]]></description>
<pubDate>2013/11/18 15:30:32</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[YI Shihe,JIANG Congfu and WANG Chengyao]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>YI Shihe,JIANG Congfu and WANG Chengyao</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200005007]]></guid><cfi:id>894</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Target Adaptive Guidance Algorithms for Homing Missile]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200005008]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Two problems are dealt with in this paper: One is how to get the distance information in passive missile guidance with bearing-only measurements; the other is the target adaptive guidance. The adaptation includes the change of the guidance aim point from the point tracked by the seeker to a vulnerable point of the target. Simulation results indicate that the algorithm is efficient.]]></description>
<pubDate>2013/11/18 15:30:32</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[QIU Ling and SHEN Zhenkang]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>QIU Ling and SHEN Zhenkang</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200005008]]></guid><cfi:id>893</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[A Study on Altitude Characteristic of Plug Nozzle Using CFD Method]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200004001]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Numerical study of plug nozzle flow field and thrust characteristic was completed based on 3-D TLA NS equations with NND2M scheme. Calculations were performed under ideal, perfect gas assumptions. Turbulence was taken into account with a k-εturbulence model. The results show a significant  performance increases at the sea level compared with the bell nozzle. They also show that NND2M scheme is fit for numerical simulation of complex jet flow.]]></description>
<pubDate>2013/11/18 15:30:46</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[GUO Zheng,LIU Jun and QU Zhanghua]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>GUO Zheng,LIU Jun and QU Zhanghua</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200004001]]></guid><cfi:id>892</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Numerical Calculation of Damping-in-Pitch Derivatives for Hypersonic Flow over Sphere-Cone Bodies]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200004002]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The full Navier-Stokes equations are adopted to describe the unsteady oscillating flow f ield over the sphere-cone. The formula of damping-in-pitch derivatives is presented under Etkin’s theory. The steady flow field is solved by the NND scheme in ADI form, and the unsteady flow field is solved by combining the four-stage Runge-Kutta scheme and implicit residual smoothing method. The numerical results are compared with experiment and ENT calculation. The tide of the derivatives varying along with the position of oscillation center is studied.]]></description>
<pubDate>2013/11/18 15:30:46</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[MOU Bin,LIU Wei and QU Zhanghua]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>MOU Bin,LIU Wei and QU Zhanghua</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200004002]]></guid><cfi:id>891</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Dynamical Strain Control of Space Structures]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200004003]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Some space structures have critical vibration problems owing to their low stiffness and low damping. And some traditional displacement control methods are no longer suitable to the space structures because they are hard to install. A new way to solve this problem has been introduced.  Both the dynamical strain equation and the strain control state equation have been developed. A cantilever beam has been taken as an example.  Numerical simulation has been done. The results show us that the vibration strain control is of great significance.]]></description>
<pubDate>2013/11/18 15:30:46</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LI Dongxu]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LI Dongxu</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200004003]]></guid><cfi:id>890</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Multizonal Numerical Simulation of Three Dimensional Hypersonic Flowfield]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200004004]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[According to the conserration of flux on the zonal boundary, a zonal boundary scheme adapted to numerical simulation of hypersonic flowfield is derived for patched grid system. Based on this work, a multizonal numerical algorithm is developed for 2D/3D supersonic and hypersonic viscous complicated flowfield. Using this algorithm, the hypersonic blunt biconic viscous flowfield is numerically simulated with the angle of attack of 0<sup>。</sup>and 4<sup>。</sup>.]]></description>
<pubDate>2013/11/18 15:30:46</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LI Hua,LIANG Jianhan and WANG Chengyao]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LI Hua,LIANG Jianhan and WANG Chengyao</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200004004]]></guid><cfi:id>889</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Analysis of Lagrange Equation Computational Method of Multibody System]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200004005]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[This paper analyzes ill-conditioned Lagrange Equation of multibody system with three degree-of-freedom rotational joint and presents a mixed pseudo coordinate lagrange's method based on constraint replacement.]]></description>
<pubDate>2013/11/18 15:30:46</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[HUANG Xinsheng,HUANG Zhengui and HUANG Kedi]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>HUANG Xinsheng,HUANG Zhengui and HUANG Kedi</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200004005]]></guid><cfi:id>888</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Operating Characteristics of Solid Ducted Rocket]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200004006]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The altitude characteristics and velocity characteristics of three types of solid ducted rocket, which are choked solid ramrocket with fixed mass flow rate of fuelrich gas generator, unchoked one and the one working under fixed mass ratio of air to fuel, were numerically studied. The results show that the performance of the unchoked ducted rocket is superior to that of the choked one. When the gas generator is loaded by  fuel-rich propellant with high exponent, the unchoked ducted rocket can almost be worked under fixed mass flow ratio of air to fuel.]]></description>
<pubDate>2013/11/18 15:30:46</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[ZHANG Wei<sup>1</sup>,FANG Dingyou<sup>1</sup>,XIA Zhixun<sup>1</sup>,ZHU Hui<sup>1</sup>,WANG Hugan<sup>2</sup> and CAI Xuanyi<sup>2</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>ZHANG Wei<sup>1</sup>,FANG Dingyou<sup>1</sup>,XIA Zhixun<sup>1</sup>,ZHU Hui<sup>1</sup>,WANG Hugan<sup>2</sup> and CAI Xuanyi<sup>2</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200004006]]></guid><cfi:id>887</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Auto-adaptable Approximation of Planar NURBS Curve with Ellipse Arc]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200004007]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[An algorithm to approximate a planar NURBS curve by ellipse-arc and bi-ellipse-arc is presented. The piecewise ellipse-arc spline calculated by this algorithm is G<sup>1</sup> continuous, and shape preserving. Compared with the present arc-approximation, this algorithm does not need equation-solving, and enable an automatic choice of parameter increment responding to the given interpolation tolerance in calculation of the character points of ellipse-arc. The algorithm also has advantage in approximation error control, which can control the approximation error to an expected one. Compared with present line-approximation mode, this algorithm, which needs no extra time and space in calculation, is applicable to CNC environment. The algorithm is specially valuable in cavity and contour machining.]]></description>
<pubDate>2013/11/18 15:30:46</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[WANG Xingbo and LI Shengyi]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>WANG Xingbo and LI Shengyi</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200004007]]></guid><cfi:id>886</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[A Quadrilateral Axisymmetric Element with Rotating Degree of freedom]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200003010]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[A quadrilateral axisymmetric element with rotating degree of freedom at the vertex nodes is derived. For improving the precision of the element, decreasing the sensitivity of element geometry and applying it to nearly incompressible materials, three nonconforming displacement functions and a “bubble” function are selected as the intemal freedom of the element. The results of the numerical examples show that the performance of the new element is fine.]]></description>
<pubDate>2013/11/18 15:30:58</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[REN Junguo<sup>1</sup> and XIONG Longfei<sup>2</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>REN Junguo<sup>1</sup> and XIONG Longfei<sup>2</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200003010]]></guid><cfi:id>885</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Molecular Dynamics Method of Scattering of the Xenon Atom from the Platinum Surface]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200003011]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Molecular dynamics method is employed for studying the scattering of xenon atom from the platinum surface. After constructing the reasonable gas-surface interaction potential energy function, the stochastic classic trajectory method is adopted to solve the motion equation of both gas atom and solid atoms, then the trajectory and velocity of gas atom can be obtained. The results show that the scattering angle distribution differs from that of Maxwellian model while the speed coincides with the half-space Maxwellian distribution.]]></description>
<pubDate>2013/11/18 15:30:58</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[HUANG Lin,CHEN Weifang,WU Qifen and REN Bing]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>HUANG Lin,CHEN Weifang,WU Qifen and REN Bing</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200003011]]></guid><cfi:id>884</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[A Study of the Optimal Feedback-Gain-Coefficients of Reentry Guidance for Spacecraft]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200003012]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Based on the nominal reentry trajectory, this paper presents the optimal feedback-gain-coefficients(FGCs) of the reentry longitudinal guidance for the return module1 First of all, the longitudinal planar motion equations are modeled. Secondly, corresponding to the longitudinal guidance law the perturbation differential equations are derived. Finally, according to the Pontryagin minimum principle, the optimal FGCs are given by solving the Riccati equation. Considering the practical feasibility, the varying gain coefficients are approximated to constant ones or gradual constant ones to form the sub-optimal FGCs. And the satisfactory guidance results are achieved.]]></description>
<pubDate>2013/11/18 15:30:58</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[TANG Guojian and ZHAO Hanyuan]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>TANG Guojian and ZHAO Hanyuan</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200003012]]></guid><cfi:id>883</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[A Research on Six Dimensional Simulation Method for Craft Trajectory Design]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200003019]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[To make the simulation result much more actual and credible, a simulation based on the actual circumstance was proposed. The cycles that must be considered in the simulation were introduced and the data-flow in the right function calculation was given Finally two kinds of simulation design and result conduct method were given. The six dimensional simulation method introduced by this paper may be useful for the design of missile, rockets or spacecraft.]]></description>
<pubDate>2013/11/18 15:30:59</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[YAN Ye and ZHAO Hanyuan]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>YAN Ye and ZHAO Hanyuan</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200003019]]></guid><cfi:id>882</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[An Algebraic Method for Fast Design of Lunar Satellite Transfer Trajectory]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200002001]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[A fast design method for the lunar satellite transfer trajectory is presented by combining patched-conic technique and ephemeris.This  method is  a pure algebraic method that doesnt need trajectory integral.It has the characteristics of rapidity and high accuracy,and can be used for preliminary design of the lunar satellite transfer trajectory.The time for precise trajectory design will be reduced greatly when parameters gotten from preliminary design is used as the initial value of precise design.]]></description>
<pubDate>2013/11/18 15:32:04</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[ZENG Guoqiang,REN Xuan and XI Xiaoning]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>ZENG Guoqiang,REN Xuan and XI Xiaoning</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200002001]]></guid><cfi:id>881</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Fusion Estimation of Normal Distribution Parameter of the Sub-missile Dispersion Center]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200002003]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[On evaluating the hitting precision of a missile which throws sub-missiles, it is a key question to estimate the normal distribution parameter of the sub-missile dispersion center. The usual method is, to find a sub-missile disper firstsion center first from each group data of the sub-missile's falling point coordinate, then to estimate the parameters according to a few data of dispersion center using the classical statistic method. Its shortcomings are the high probability to make a wrong conclusion. Considering that the sub-missile dispersion center, which cannot  sufficiently express the information contained in the sub-missile falling point data group, is only its first moment, in this paper a new method on fusion estimating the distribution parameter is researched.]]></description>
<pubDate>2013/11/18 15:32:04</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[XIA Shengping<sup>1</sup>,XIE Hongwei<sup>1</sup>,WAN Bo<sup>2</sup> and CAO Guomin<sup>2</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>XIA Shengping<sup>1</sup>,XIE Hongwei<sup>1</sup>,WAN Bo<sup>2</sup> and CAO Guomin<sup>2</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200002003]]></guid><cfi:id>880</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[A New Method of Measure the Pitching and Yaw of the Axes Symmetry Object through the Optical Image]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200002004]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[A new method for measurement of the pitching angle and yaw angle of an axes-symmetric object through the optical images is presented, and the accuracy of the method is analyzed. This method is highly accurate because a large amount of information of the object image is used. The difficulty of object matching among several images is avoided since the object's axis is measured in an indirect way.]]></description>
<pubDate>2013/11/18 15:32:04</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[YU Qifeng,SUN Xiangyi and CHEN Guojun]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>YU Qifeng,SUN Xiangyi and CHEN Guojun</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200002004]]></guid><cfi:id>879</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[High Order Accurate WENO Schemes for the 2D Flowfield of Shock-Boundary Layer Interaction]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200002005]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The time-dependent numerical method is used to solve Navier-Stokes equations and simulate the 2D shockwave planar boundary-layer interaction.  In our computation, the high order accuracy WENO schemes are applied to pursuing numerical approximation of the inviscid spatial derivative. To step on time, we make use of the Runge-Kutta methods with property of TVD. The viscous term is discremeted by two-order central difference scheme. The resultant pressure and shear distribution agree with those of the experiments. The numerical practice shows the WENO schemes are robust and strong indeed, and have a vast range of prospects for application.]]></description>
<pubDate>2013/11/18 15:32:04</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[XU Wanwu,WANG Zhenghua,HOU Zhongxi and WANG Chengyao]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>XU Wanwu,WANG Zhenghua,HOU Zhongxi and WANG Chengyao</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200002005]]></guid><cfi:id>878</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Software Fire Table Applied in Meteorological Rocket Launch]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200002006]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Before launching a meteorological rocket, the fire table must be used for wind correction to the rocket's flight trajectory. The traditional fire table has defects in accuracy and generality. Based on numerical simulation of the flight trajectory and the technology of search and iteration, software fire table determines the launching angle and flight trajectory by satisfying specific requirements at detach point, and makes improvement in accuracy and generality.]]></description>
<pubDate>2013/11/18 15:32:04</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[CHEN Guangnan and ZHANG Weihua]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>CHEN Guangnan and ZHANG Weihua</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200002006]]></guid><cfi:id>877</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Combustion Effect on the Reattachment Point in Solid Fuel Ramjet]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200002007]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Cold flow field and simple-reaction flow field of the combustion of HTPB and PS within the solid fuel ramjet (SFRJ) are simulated using PHOENICS program. The result shows that the reattachment point moves forward so that the flow field structure is altered in case of combustion. In case of cold flow, the reattachment point doesn't change with inlet temperature, but it does so in simple-reaction flow field. And it doesn't change with inlet mass flux in both conditions.]]></description>
<pubDate>2013/11/18 15:32:04</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[TAN Jianguo,CHEN Xiaoqian,YANG Tao and ZHANG Weihua]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>TAN Jianguo,CHEN Xiaoqian,YANG Tao and ZHANG Weihua</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200002007]]></guid><cfi:id>876</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Monte Carlo Transport of Electrons in Matter]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200001020]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[This paper introduces the basic principles and steps of the Monte Carlo Methods used in the electron transport calculation. The electron transport process is simulated by “condensed history” Monte Carlo method. The electron random walk path length is determined by the energy steps. For a single step, the electron energy loss is the total amount of the nonradiative (collisional) energy loss and radiative (bremsstrahlung) energy loss, the nonradiative energy loss in each step is sampled from Landau formulation, and the radiative energy loss and the production of bremsstrahlung photon is sampled from Bethe-Heitler formulation. The direction of electron at the end of each step is sampled from the Gouddsmit-Saunderson multiple scattering formulation. The Moller cross section is used for the sampling of the electron-electron scattering. Finally the electron transport in the space used aluminum alloy, and plane materials is calculated and the results are presented.]]></description>
<pubDate>2013/11/18 15:30:11</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[WANG Tongquan,ZHANG Shufa,WANG Shangwu and SHEN Yongping]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>WANG Tongquan,ZHANG Shufa,WANG Shangwu and SHEN Yongping</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200001020]]></guid><cfi:id>875</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Numerical Distributed Transfer Function Method for Planar Optical Waveguides]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200001021]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Numerical distributed transfer function method is applied to planar optical waveguides. By using scalar variational principle, the numerical transfer function equations are derived. Then problems are solved in the form of state space. Infinite elements are introduced to reduce the amount of computation. This is more reasonable in the near cut-off case. Application and numerical examples are given and compared with several other methods which show the advantage of this method on planar optical waveguides with either step or graded refractive index profile.]]></description>
<pubDate>2013/11/18 15:30:12</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LI Haiyang<sup>1</sup>,FENG Ying<sup>2</sup> and ZHOU Jianping<sup>1</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LI Haiyang<sup>1</sup>,FENG Ying<sup>2</sup> and ZHOU Jianping<sup>1</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200001021]]></guid><cfi:id>874</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[The Application of Preconditioning in Viscous Flow at Low Speeds]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200001022]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The time-dependent method&LU-SGS implicit scheme has been used to solve 2D compressible Navier-Stokes equations which are preconditioned and simulate the driven cavity flow field at different low Mach numbers and different Reynold numbers. To apply the time-dependent method to simulate the flow field at low speeds validly and accelerate the convergence rates, a matrix called preconditioning matrix has multiplied the time-derivative terms of Navier-Stokes equations. This is known as preconditioning. Convergence rates are accelerated for a certainty, while providing solutions are identical to those obtained without preconditioning methods. The results are compared with available data.]]></description>
<pubDate>2013/11/18 15:30:12</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LIAO Shouyi,WANG Zhenghua and WANG Chengyao]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LIAO Shouyi,WANG Zhenghua and WANG Chengyao</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200001022]]></guid><cfi:id>873</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[A Method of Measuring Flyer Velocity and Impact Slant in Plane Dynamic Loading Experiments]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200001023]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In plane dynamic loading experiments, the velocity of flyer and state of impact are key parameters of loading condition. A technique of electric pins for measuring the above parameters is designed, aiming at deducing a real velocity of flyer and slant of impact from local records of pins signs through a certain arrangement of the pins. The method has been used in experiments of shock activating Si<sub>3</sub>Ni<sub>4</sub> powder materials, and the results are satisfactory.]]></description>
<pubDate>2013/11/18 15:30:12</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LU Fangyun,CAI Qingyu,CHEN Gang,WANG Zhibin and ZHANG Zhengyu]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LU Fangyun,CAI Qingyu,CHEN Gang,WANG Zhibin and ZHANG Zhengyu</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200001023]]></guid><cfi:id>872</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Simulation of Shock Propagation in Baffle Systems by Unstructured Euler Method]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200106001]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Flows of 2-D shock propagation in single or multiple baffle systems are simulated. Euler equations are solved numerically by NND finite volume scheme in unstructured triangular grids. The results show clearly the complex structure of the flowfields and compare well with experimental data. It is demonstrated that unstructured grid method can handle these complex geometries easily and avoid probable unreasonable solution near the sharp corner.]]></description>
<pubDate>2013/8/21 0:00:00</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[GUO Zheng,LIU Jun and QU Zhanghua]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>GUO Zheng,LIU Jun and QU Zhanghua</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200106001]]></guid><cfi:id>871</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Numerical Simulation of 3D Turbulent Vortex Structures in Isolator]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200106002]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The interaction between shock waves and boundary layer in isolator causes a very complicated flow, to simulate the turbulent flow field in it, the time-dependent, implicit, finite volume, lower-upper numerical method was used to solve the 3D compressible Reynolds-averaged Navier-Stokes equations. Numerical results are compared with experimental data and used to describe the vortex structures in different isolator shape or different location of an isolator combined shock train structures in it. The numerical results indicate that the vortex structures in square cross section and rectangular cross section is very different.]]></description>
<pubDate>2013/8/21 9:51:18</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[FAN Xiaoqiang,LI Hua and DING Meng]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>FAN Xiaoqiang,LI Hua and DING Meng</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200106002]]></guid><cfi:id>870</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Variation of SMD for Atomization of Model Tripropellant Injectors]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200106003]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In order to study completely the atomization characteristics of mixing cavity of the designed new type tripropellant injectors, model injectors are designed for experiments under multiple operating conditions. Through experiments it can be seen that different curves of regularity for variations of SMD along with pressure drop of gas as well as mass ratio of gas to liquid ALR will be gain if the pressure drop of liquid remains constant while transform the pressure drop of gas. So do the other case only transforming the pressure drop of liquid. Moreover, these curves show the regularities. A great deal of experiments indicate the curves of average diameters SMD along with mass ration of gas to liquid ALR have the same trends although obvious differences exist between curves that SMD along with pressure drop.]]></description>
<pubDate>2013/8/21 9:51:18</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LI Qinglian,TIAN Zhangfu and WANG Zhenguo]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LI Qinglian,TIAN Zhangfu and WANG Zhenguo</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200106003]]></guid><cfi:id>869</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[A Hexahedron Generalized Conforming Element with High Accuracy]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200106004]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In this paper a normal freedom on each area is given on 8-node hexahedron isopapametric element. At the same time seven unconforming inner displacement functions and one bubble function are adopted as additional displacement in order to eliminate geometry sensitivity and gain high precision. Numerical results show that this element is of excellent properties.]]></description>
<pubDate>2013/8/21 9:51:18</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[REN Junguo,ZHANG Shujun and OUYANG Yong]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>REN Junguo,ZHANG Shujun and OUYANG Yong</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200106004]]></guid><cfi:id>868</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Combustion Characteristics of Silver-Wire Embedded Fuel-Rich Propellant]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200106005]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The combustion characteristics of silver-wire embeded fuel-rich propellant grain are investigated. The effect of the diameters of silver wires and the composition of the propellant on the combustion properties is studied. The test pressure-time curves show that the combustion process of silver-embedded fuel-rich grain consiss of initial part, steady part and end part. The silver-embedded fuel-rich propellant grain with coarse silver wire（diameter: 0.3mm and 0.4mm）gives up high burning rate. Furthermore, to increase the burning rate of the fuel-rich propellant is also a good way to increase the burning rate of the silver-embedded fuel-rich propellant grain.]]></description>
<pubDate>2013/8/21 9:51:18</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[ZHANG Wei<sup>1</sup>,ZHU Hui<sup>1</sup>,XIA Zhixun<sup>1</sup>,FANG Dingyou<sup>1</sup>,ZHU Baohua<sup>2</sup> and CAO Junwei<sup>2</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>ZHANG Wei<sup>1</sup>,ZHU Hui<sup>1</sup>,XIA Zhixun<sup>1</sup>,FANG Dingyou<sup>1</sup>,ZHU Baohua<sup>2</sup> and CAO Junwei<sup>2</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200106005]]></guid><cfi:id>867</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[The Prediction of Fluctuating Pressure on the Surface of Reentry Vehicles]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200106006]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The fluctuating pressure distribution on the surface of the sphere-biconic reentry vehicle in a wide range of attack angles is investigated in the supersonic and hypersonic flow field. Based on the mean pressure distribution, some engineering correlation has been developed. Then utilizing the developed techniques, we investigate the effects of Mach number, attack angle and wall temperature and achieve a series of reasonable results comformable to test data.]]></description>
<pubDate>2013/8/21 9:51:18</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[CHEN Weifang,ZHANG Zhicheng,SHI Yuzhong,WANG Quanli and WU Qifen]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>CHEN Weifang,ZHANG Zhicheng,SHI Yuzhong,WANG Quanli and WU Qifen</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200106006]]></guid><cfi:id>866</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[The Design and Simulation of A Cruise Aircraft Control System]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200106007]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[This paper mainly describes the method of designing a aircraft control system based on the classical control theory after creating the aircraft movement models. The control system's performance is also simulated with the effects of some nonlinear elements such as saturation and transport delay. From the results we can see that the structure and parameters are reasonable, the performance can meet the need of the task. At the same time, it can offer more creditable data and diagram for the hardware-in-the-loop simulation and the flight experiment.]]></description>
<pubDate>2013/8/21 9:51:18</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LIAO Ying and WANG Jing]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LIAO Ying and WANG Jing</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200106007]]></guid><cfi:id>865</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Kalman Filter Design for Multi-sensors Satellite Attitude Determination]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200106008]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Aiming at satellite attitude system which is composed of gyroscopes, infrared earth sensors and solar sensors, we set up the model of the satellite attitude detemination by using quaternion, and build kalman filter for information fusion. The simulation result indicates that this method can provide satellite attitude parameters which satisfy the requirement.]]></description>
<pubDate>2013/8/21 9:51:18</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LIU Zhijian,WU Meiping and HU Xiaoping]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LIU Zhijian,WU Meiping and HU Xiaoping</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200106008]]></guid><cfi:id>864</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Navigation for the Lunar Probe Based on Ground Tracking Sites]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200106009]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Taking an lunar probe around the earth and the moon from the earth parking orbit for example, we analyze some questions of navigation of the lunar probe based on ground tracking site, including the choice of tracking type, distribution of ground tracking site, adjustment of the guiding time, and accuracy of navigation. It is verified that the lunar probe can be navigated in real-time by ranging data based on the local ground tracking site. The method and result of the research may serve as reference for the practical engineering of lunar probe.]]></description>
<pubDate>2013/8/21 9:51:18</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[WEN Yuanlan<sup>1</sup>,WANG Wei<sup>2</sup>,ZENG Guoqiang<sup>1</sup> and XI Xiaoning<sup>1</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>WEN Yuanlan<sup>1</sup>,WANG Wei<sup>2</sup>,ZENG Guoqiang<sup>1</sup> and XI Xiaoning<sup>1</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200106009]]></guid><cfi:id>863</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Self-adaptive Spline Filter Approach for Trajectory Determination by Velocity Measurement]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200106010]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Based on spline filtering, this paper presents a novel self-adaptive approach for trajectory determination by using velocity measurements. The spline function is adopted to express the parameters of the trajectory so that an iterative algorithm of self-adaptive Kalman filter is established. When information of velocity measurement is merely provided, this approach can give real-time trajectory parameters of the aircraft with high precision.]]></description>
<pubDate>2013/8/21 9:51:18</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[ZHOU Haiyin,WANG Xiongliang and ZHU Jubo]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>ZHOU Haiyin,WANG Xiongliang and ZHU Jubo</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200106010]]></guid><cfi:id>862</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Several Calculating Problems of theProcessing of Trajectory Tracking Data]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200106011]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Based on our research and exploration in the field of data processing and modeling of trajectory tracking data, this paper puts forward several observing data models with typical application. These models are relative to many aspects of statistics, optimization, functional approximation in theory and calculation. The investigation of these problems and models is significant to the solution of many relevant practical problems.]]></description>
<pubDate>2013/8/21 9:51:18</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[WANG Zhengming,ZHOU Haiyin,TONG Li,ZHU Jubo and DUAN Xiaojun]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>WANG Zhengming,ZHOU Haiyin,TONG Li,ZHU Jubo and DUAN Xiaojun</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200106011]]></guid><cfi:id>861</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[The Study of Free Flight Phase Trajectory Estimation]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200106012]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[By using the line of sight (LOS) measurements from space-based infrared sensors, free flight phase trajectory estimation problem of ballistic missile is studied. Taking into account poor target motion observability, maximum likelihood estimation problem of trajectory is solved by using an improved Gauss-Newton algorithm by which the position and velocity are filtered in turn. Monte Carlo stimulation verifies the efficiency of this algorithm. Besides estimation error is analyzed.]]></description>
<pubDate>2013/8/21 9:51:18</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LI Dun,ZHOU Yiyu,LU Tongguang and MIAO Yu]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LI Dun,ZHOU Yiyu,LU Tongguang and MIAO Yu</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200106012]]></guid><cfi:id>860</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Solving Orbital Transformation and Interception Problems Based on EA]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200105001]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[With diversiform needs of space missions,not only minimizing fuel is required for the spacecrafts interception and orbit transformation, but minimizing time is also required.In this paper, the combinatorial optimization problem is solved by EA(Evolution Algorithm),and the algorithm  proves to be effective according to the simulation results.]]></description>
<pubDate>2013/8/21 9:51:31</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[WANG Shi,ZHU Kaijian,DAI Jinhai and REN Xuan]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>WANG Shi,ZHU Kaijian,DAI Jinhai and REN Xuan</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200105001]]></guid><cfi:id>859</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Miss Distance Measurement for Targets with RectilinearTrajectories and Constant Velocities]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200105002]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The miss distance measurement for targets in rectilinear motion and with constant velocities is studied. A miss distance measurement mathematical model is established at first. Based on it, the measurement problem is represented as the nonlinear fitting of radial distance time series in the course of interceptions, and then optimizing algorithms are discussed for solving it. Simulations show that the method for miss distance measurement based on radial distance time series is simple and effective.]]></description>
<pubDate>2013/8/21 0:00:00</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[SHAN Yuehui,LOU Shengqiang and HUANGFU Kan]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>SHAN Yuehui,LOU Shengqiang and HUANGFU Kan</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200105002]]></guid><cfi:id>858</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Cooperative Coevolutionary Multidisciplinary Design Optimization of Missile System]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200105003]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Traditional missile design procedure cannot achieve synergic design of subsystems well. Multidisciplinary design optimization technique is very suitable for multidiscipline synergic design in modern computer network environment. We introduce coevolutionary algorithms to multidisciplinary design optimization based on their substantial similarity, to sufficiently employ the merit of evolutionary algorithmsin MDO. A multidisciplinary design optimization method based on cooperative coevolutionary algorithms is presented. The algorithm is applied to missile aerodynamic/engine/control multidisciplinary design optimization, and result shows it's ability in design optimization of coupled systems.]]></description>
<pubDate>2013/8/21 9:51:31</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[CHEN Qifeng,LI Xiaobin and DAI Jinhai]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>CHEN Qifeng,LI Xiaobin and DAI Jinhai</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200105003]]></guid><cfi:id>857</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Assessment for the Accuracy of the Fall Points—Probability Circle Method]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200105004]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The performance of the missiles is determined mostly by the accuracy and dispersion of the random fall points. In small samples case, it is difficult to assess respectively the accuracy and dispersion. The integration assessment approach adopting probability circle method is proposed. The performance is accepted when the number which fall into the probability circle is larger than or equal to the number predetermined, otherwise it is rejected. The producer's risk and consumer's risk are also given. Finally, the simulation shows that the approach proposed in this paper is available. Probability circle method is simple and easy for practical applications.]]></description>
<pubDate>2013/8/21 9:51:31</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[CHENG Guangxian<sup>1</sup> and ZHANG Shifeng<sup>2</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>CHENG Guangxian<sup>1</sup> and ZHANG Shifeng<sup>2</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200105004]]></guid><cfi:id>856</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Three-Axis Magnetometer Attitude Determination]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200105005]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Satellitestend to be micromation in future. Itis necessary to investigate small, cheap self-contained navigation system with moderate precision. According to measuring data of three-axis magnetometer in the body frame, the attitude of the satellite in low orbit can be determined through Kalman Filter. Combining the dynamical model of satellite's attitude with the standard model of the geomagnetic field,the filter model and arithmetic used to determine the attitude of the satellite are presented. The result of simulation shows that the project of three-axis magnetometer attitude determination has a certain precision, which has an applicable future in the self-contained navigation system with moderate precision attitude determination.]]></description>
<pubDate>2013/8/21 9:51:31</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[TIAN Jing,WU Meiping and HU Xiaoping]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>TIAN Jing,WU Meiping and HU Xiaoping</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200105005]]></guid><cfi:id>855</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[The Study of Human Behavior Modeling for Air Combat of Two Fighters]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200105006]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The reality of human behavior model is critical for the CGF.A three-layer human behavior model based on the fuzzy rule is first proposed for one vs. one fighter dogfight and the fuzzy-flight-state controller on the bottom layer was optimized using genetic algorithms. The simulation result suggest that this model can generate human-like air combat behavior.]]></description>
<pubDate>2013/8/21 9:51:31</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[BO Tao,YIN Juan,WANG Zhengzhi and HUANG Kedi]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>BO Tao,YIN Juan,WANG Zhengzhi and HUANG Kedi</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200105006]]></guid><cfi:id>854</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Numerical Analysis of the Effects for DifferentThermo-chemical Models on Heat Transfer]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200105007]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The effects of different thermo-chemical air models and surface catalytic conditions on surface heat transfer are analyzed numerically. They include (1) the comparison of different high temperature air models (7 species and 11 species), (2) the comparison of chemical nonequilibrium flow with thermo-nonequilibrium (two temperature model) and thermo-equilibrium (one temperature model), (3) the comparison of different surface catalytic condition.]]></description>
<pubDate>2013/8/21 9:51:31</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[ZENG Ming,FENG Haitao and QU Zhanghua]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>ZENG Ming,FENG Haitao and QU Zhanghua</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200105007]]></guid><cfi:id>853</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[A UL Formulation for Cables]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200105008]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[A convergent iterative solution method for cables is formulated after solving the boundary problem with differential equation of a cable. By using the iterative solution, it is simple to determine the relation among the coordinate difference of cable-end position, cable tension and cable weight. The examples demonstrate that the present scheme for cable calculation can be as theoretically concise as required, and it is convenient to be used for analysing largely deformed complicated structures including cables or cable nets, and the present method makes it possible to solve the divergence problem of stress relieve of cables caused by employing some techniques such as Ernst Model for cables.]]></description>
<pubDate>2013/8/21 9:51:31</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[XIAO Wanshen<sup>1,2</sup>,ZENG Qingyuan<sup>3</sup> and TANG Guojin<sup>1</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>XIAO Wanshen<sup>1,2</sup>,ZENG Qingyuan<sup>3</sup> and TANG Guojin<sup>1</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200105008]]></guid><cfi:id>852</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Modeling and Numerical Study on the Shock-induced Fluidization of Inert Powder Layers by the Granular Flow Models]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200104001]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The granular flow models on the basis of the kinetic theory are presented for numerical study on a dense particles bed with shock interaction. For the solid phase, the constitude equations are deduced from the interactions between the mean and the fluctuating motions of solid particles,the latter are represented as functions of the granular flow temperature. Numerical simulation by the AUSM<sup>+</sup> schemes is employed to analyse the flowfield of the shock-induced fluidization of inert powder layers. It shows that the granular flow models are feasible to describle the flow with high speed and strong discontinunity.]]></description>
<pubDate>2013/8/21 9:51:44</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LI Jie<sup>1</sup>,CHEN Weifang<sup>1</sup>,REN Bin<sup>1</sup> and FAN Baochun<sup>2</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LI Jie<sup>1</sup>,CHEN Weifang<sup>1</sup>,REN Bin<sup>1</sup> and FAN Baochun<sup>2</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200104001]]></guid><cfi:id>851</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Analysis and Design of Three Satellites Cluster for Time-difference Localization]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200104002]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[This paper brings forward the principle of designing three satellites cluster for time-difference localization according to the analysis of positioning precision. It analyses the geometry transformation of the cluster, and discusses the design of global localization cluster. An efficient designing method is given in the end. It is proved by simulation that the satellites cluster designed by this method can provide global high-precision localization.]]></description>
<pubDate>2013/8/21 9:51:44</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[WANG Haili,CHEN Lei and REN Xuan]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>WANG Haili,CHEN Lei and REN Xuan</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200104002]]></guid><cfi:id>850</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Multizonal Numerical Simulation of Jet Flowfield of a Launch Escape Vehicle]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200104003]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[According to the conservation of flux on the zonal boundary,a two and three dimensional zonal boundary schemes are derived for patched grid systems.Based on this work,a multizonal numerical algorithm is developed for 2D/3D viscous complicated flow field with supersonic jet.Using this algorithm,the Launch Escape Vehicle (LEV) jet interaction viscous flow field is numerically simulated with angle of attack of 4°and 8°.]]></description>
<pubDate>2013/8/21 9:51:44</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LI Hua,LIANG Jianhan and WANG Chengyao]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LI Hua,LIANG Jianhan and WANG Chengyao</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200104003]]></guid><cfi:id>849</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Numerical Simulation and Validation of 3D Hypersonic Jet Interaction Flowfield]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200104004]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[A numerical method has been developed to solve the three dimensional Navier-Stokes equations and the numerical procedure uses Osher-Chakraverthy's TVD scheme for the inviscid flux and central difference scheme for the viscous flux. LU-SSOR method is used to solve the resulting systems of discretized equations and the Baldwin-Lomax turbulent model is used. Numerical solutions of three dimensional hypersonic jet interaction flow field with angle of attack of 5° is obtained and experimentally validated this numerical result at KD-01 gun wind tunnel. By validating, some problems of numerical simulation are studied.]]></description>
<pubDate>2013/8/21 9:51:44</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LI Hua,WANG Chengyao,YI Shihe and CHENG Zhongyu]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LI Hua,WANG Chengyao,YI Shihe and CHENG Zhongyu</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200104004]]></guid><cfi:id>848</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Reliability Demonstration Testing Procedure for Weibull Distribution]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200104005]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The reliability demonstration testing procedure for Weibull distribution is discussed.First,the noninformative prior distribution of the parameters of the life distribution is derived.Then the prior PDF(Probability Density Function) of these parameters are given combining with prior information according to Bayesian theorem. Finally,the reliability demonstration testing procedure is analyzed taking into consideration the consumer's profit and producer's profit. The simulation results show that the consumer's profit and producer's profit can be compromised.]]></description>
<pubDate>2013/8/21 9:51:44</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[ZHANG Shifeng]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>ZHANG Shifeng</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200104005]]></guid><cfi:id>847</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Sphere-Cone Pressure Prediction in Supersonic/Hypersonic Flow]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200104006]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The method applied to sphere-cone pressure prediction has been extended to calculate pressure distribution on sphere-bicone vehicles in supersonic/hypersonic flow field. The results under various flow conditions compare favorably with numerical flow field solutions and the wind tunnel test data.]]></description>
<pubDate>2013/8/21 9:51:44</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[ZHANG Zhicheng,CHEN Weifang and SHI Yuzhong]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>ZHANG Zhicheng,CHEN Weifang and SHI Yuzhong</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200104006]]></guid><cfi:id>846</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[An Element Model with Strip Distributed Transfer Function Method for Elastic Thin Plates]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200103001]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Using modified strip distributed transfer function method, a strip element model with two nodal lines and four degrees of freedom is built for the analysis of static response. The rectangular region is divided into strips by nodal lines. The border lines are discrete. The displacements and angles of the inner lines and boundary nodes are unknown. An super element, which can couple with finite elements, is given using cubic interpolation. By using generalized function, an accurate integration method is developed to get the explicit formulation of the matrixes involved. This can improve the accuracy and efficiency of the method.]]></description>
<pubDate>2013/8/21 9:52:03</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LI Haiyang,LEI Yongjun and ZHOU Jianping]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LI Haiyang,LEI Yongjun and ZHOU Jianping</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200103001]]></guid><cfi:id>845</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[A General Solution of Free Vibration for Rectangular Thin Plates on the Elastic Foundation]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200103002]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[A general solution of differential equation for transverse displatement function in free vibration of rectangular thin plate on elastic foundation is obtained. It can be used to solve the vibration problem of rectangular plate with arbitrary boundaries. For example, a square plate with two adjacent edges fixed and other two free have been calculated.]]></description>
<pubDate>2013/8/21 9:52:03</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[HUANG Yan and LIU Daquan]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>HUANG Yan and LIU Daquan</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200103002]]></guid><cfi:id>844</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[On Chemical Non-equilibrium 3D-VSL Flow]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200103005]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The chemical non-equilibrium three-dimensional viscous shock layer flows are calculated numerically. The coupled solutions of the chemical non-equilibrium viscous shock layer flows are obtained through space-marching and global iterations.]]></description>
<pubDate>2013/8/21 9:52:03</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[SHI Yuzhong,CHEN Weifang,WU Xiong and ZHANG Zhichen]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>SHI Yuzhong,CHEN Weifang,WU Xiong and ZHANG Zhichen</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200103005]]></guid><cfi:id>843</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[GPS Navigation of the Lunar Probe in the Close Earth Orbit Phase]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200102001]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The lunar probe requires accurate information on position and velocity when it runs on its close phase of orbit. Dynamical estimation with GPS can provide the accuracy needed. This paper presents a description of the conditions about choosing the GPS satellites and the numbers of the available GPS satellites on close phase of orbit, the solutions of dynamical method with GPS, and the influences with different sampling intervals and force models. The results show that the dynamical method with GPS can meet the precision requirement with reduced force models and 5s sampling interval.]]></description>
<pubDate>2013/8/21 9:52:17</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[WANG Wei,WEN Yuanlan,ZENG Guoqiang and XI Xiaoning]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>WANG Wei,WEN Yuanlan,ZENG Guoqiang and XI Xiaoning</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200102001]]></guid><cfi:id>842</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Robust Kalman Filtering for Satellite Orbit Determination]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200102003]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Kalman filtering is affected by the gross error that is inevitable in the observation of satellite. First robust kalman filtering is derived and its robustness is analyzed, then the observations of Lageos is processed. It verifies that robust kalman filtering has the capability to resist the gross error.]]></description>
<pubDate>2013/8/21 9:52:17</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[WEN Yuanlan<sup>1</sup>,WANG Wei<sup>1</sup> and YANG Yuanxi<sup>2</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>WEN Yuanlan<sup>1</sup>,WANG Wei<sup>1</sup> and YANG Yuanxi<sup>2</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200102003]]></guid><cfi:id>841</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Quick Ambiguity Solution by Geometrical Constraints]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200102004]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[On the basis of application of GPS carrier phase measurements to determinate the carrier's attitude, focusing on its key technical problem—fast determination of carrier phase ambiguity,a method which makes full use of geometric constraints among GPS satellites and baseline to compress search space in order to acquire the correct double differential ambiguity quickly has been developed. A simulation experiment using the rude statistics received by ADUⅡ attitude determination receiver shows that it is a practical ambiguity resolution.]]></description>
<pubDate>2013/8/21 9:52:18</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LU Liangqing and HU Xiaoping]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LU Liangqing and HU Xiaoping</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200102004]]></guid><cfi:id>840</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Research on Generalized Two-Point Boundary-Value Problem Based on Neural Network]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200102005]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[A great number of guidance problems can be considered the problems of generalized two-point boundary-value in the field of aerospace. The paper discusses the methods to solve these problems with the help of neural network. The static two-point boundary-Value problems, such as offline guidance, are discussed in the paper. Based on the discussion, the dynamic two-point boundary-value problems, such as online guidance, are analyzed, and an effective method to solve them is presented.]]></description>
<pubDate>2013/8/21 9:52:18</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[CHEN Lei,WANG Haili and REN Xuan]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>CHEN Lei,WANG Haili and REN Xuan</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200102005]]></guid><cfi:id>839</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Damage Model of Air-to-Surface Missile Target Based on Finite Elements]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200102006]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Damage rules, target structrue and damage trees are proposed first. Finite elements are utilized to partition the shape of target. A vulnerability model of missile with fragmentation warhead damaging the target is built. With the validity of the simulation algorithm, the vulnerability model of the missile-launching vehicle is researched into and its result is given. From the result of the simulation, the damaging course of the  missile attaching the targets on the ground can be depicted.]]></description>
<pubDate>2013/8/21 0:00:00</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[WANG Hongwei,HE Hangen and HUANG Kedi]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>WANG Hongwei,HE Hangen and HUANG Kedi</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200102006]]></guid><cfi:id>838</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Numerical Simulation about the Process that a Shock Wave Inducesthe Combustible Gas Deflagrating]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200102007]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Based on the theory of reaction fluid dynamic, numerical simulate about the process that shock waves induce the combustible gas deflagrating in one-dimensional system with the chemical model of nine equation is successfully accomplished. The generation mechanism of the induced process and an important effect of shock waves extinguishing the forest fire are clearly interpreted by the density variety of CO and the variety of pressure and temperature in the field.]]></description>
<pubDate>2013/8/21 9:52:18</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[ZHANG Yan,REN Bing,CHANG Xiyu and XIONG Guoqing]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>ZHANG Yan,REN Bing,CHANG Xiyu and XIONG Guoqing</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200102007]]></guid><cfi:id>837</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Research on Coherent Anti-stokes Raman SpectroscopyMeasurement Technology]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200102008]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In order to apply Coherent Anti-stokes Raman Spectroscopy(CARS)to combustion diagnosis, this paper studied correlation between theoretical CARS and temperature, correlation between theoretical CARS and concentration and correlation between theoretical CARS and pressure. Also, LPG/air flame temperature was measured with N<sub>2</sub> CARS]]></description>
<pubDate>2013/8/21 9:52:18</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LI Mailiang,ZHAO Yongxue,GENG Hui,ZHOU Jin and WANG Zhenguo]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LI Mailiang,ZHAO Yongxue,GENG Hui,ZHOU Jin and WANG Zhenguo</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200102008]]></guid><cfi:id>836</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Set up the Granule Flow Equations by the Method of the Generalized BGK Model]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200102009]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The granule flow equations are deduced from the generalized BGK model. The generalized BGK equation is treated with the Chapman-Enskog method that is used in the classic molecular kinetics. The equations are easily generalized since the method is simple and the quantities in them have concise physical meaning.]]></description>
<pubDate>2013/8/21 9:52:18</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[CHEN Weifang,LI Jie,WANG Quanli,REN Bin and FAN Baochun]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>CHEN Weifang,LI Jie,WANG Quanli,REN Bin and FAN Baochun</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200102009]]></guid><cfi:id>835</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Numerical Study on the Interaction of a Planar Shock Wave Sweeping a Density Layer with the Interface]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200102010]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[When a planar shock wave is sweeping a density layer, the deformation of the density interface and the wave configurations can occur. Numerical simulations about this process for high density layer is proposed. The result based on TVD scheme is checked using analytical simulations, It shows that the interaction of the shock wave with the high density layer can induce the wave reflection from the wall which is either a stationary regular reflection or a stationary Mach reflection.]]></description>
<pubDate>2013/8/21 9:52:18</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LI Jie,REN Bing,ZHANG Yan and CHEN Weifang]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LI Jie,REN Bing,ZHANG Yan and CHEN Weifang</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200102010]]></guid><cfi:id>834</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Boundary Conditions for Solving Flowfields at Low Mach Numbers by Preconditioning]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200102011]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The influences of three common boundary conditions at low speed entrance on stability and convergence are present by solving 2-D compressible Euler equations that have been preconditioned. The test shows that by preconditioning the boundary condition based on the Riemann invariants at low Mach numbers is reflective boundary condition while the other two are unreflective boundary conditions.]]></description>
<pubDate>2013/8/21 9:52:18</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LIAO Shouyi and WANG Chengyao]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LIAO Shouyi and WANG Chengyao</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200102011]]></guid><cfi:id>833</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Fracture Features of Interfacial Crack of Ⅲ Type in Bi-material of Visco-elasto-plasticity]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200102012]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Dugdale-Barenblatt model is extended to analyse the problem of the crack on the interface between two viscoelastoplastic materials. After the governing equations are Fourier-transformed, the problem of boundary conditions with tangential jumps trans-formed into singular integral equations by using sectional definite-integral transformation. Following solving the integral equations are the formulation of the length of the plastic zone (LPZ) ahead of the crack tip and crack-tip opening displacement (COD), and the derivation of the strain energy release rate. Results reveal that the LPZ and COD are both determined by the minimum yielding stress of the two constituent materials, and the latter also rises at a gradually declining speed as time increases.]]></description>
<pubDate>2013/8/21 9:52:18</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[XIAO Wanshen<sup>1,3</sup>,TANG Guojin<sup>3</sup> and TANG Songhua<sup>2</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>XIAO Wanshen<sup>1,3</sup>,TANG Guojin<sup>3</sup> and TANG Songhua<sup>2</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200102012]]></guid><cfi:id>832</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[A Comparison of Numerical Computational Methods for Unsteady Supersonic Flow]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200101001]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The implicit varied coefficient residual smoothing technology was introduced into the four-stage Runge-Kutta scheme to increase the computational efficiency for unsteady supersonic flow under keeping second order accuracy in time and space. The computational results achieved by four-stage Runge-Kutta scheme and dual-time method were compared through numerical simulation unsteady harmonic oscillating flow around sphere-cone.]]></description>
<pubDate>2013/8/21 9:52:31</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LIU Wei and MOU Bin]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LIU Wei and MOU Bin</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200101001]]></guid><cfi:id>831</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Transfer Function Analytic Method for Stochastic Beams]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200101003]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The transfer function method is combined with the traditional spectral approach theory. The stochastic field is expanded by orthonormal Karhunen-Loeve method, the static stochastic beam analyzed and its credibility reckoned in the end. This method conquer the difficulty of the huge numerical computation of the traditional finite element method and an analytical analysis method of stochastic structure analysis is formed.]]></description>
<pubDate>2013/8/21 9:52:31</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[OUYANG Yong,REN Junguo and ZHOU Jianping]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>OUYANG Yong,REN Junguo and ZHOU Jianping</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200101003]]></guid><cfi:id>830</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Numerical Simulation of Shock Train in a Constant Area Isolator]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200101004]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[A finite volume method is used to simulate the shock train flows in a generic two-dimensional constant area isolator. Isolator is an important components of Dual-Mode scramjet. The interaction between a normal shock wave and a boundary layer along a wall surface in isolator compressible flows causes a very complicated flow. The interaction region including a shock train and a mixing region in it is referred to as “pseudo-shock”. The finite volume method is used to solve the 2D Reynolds-averaged Navier-Stokes equation coupling the Baldwin-Lomax zero-equation turbulence model. In the numerical procedure, LUSGS method and TVD scheme are used. The numerical results simulate commendably the topology structure of the flows.]]></description>
<pubDate>2013/8/21 9:52:31</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[DING Meng,LI Hua and FAN Xiaoqiang]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>DING Meng,LI Hua and FAN Xiaoqiang</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200101004]]></guid><cfi:id>829</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Numerical Study of Electron Density in the Plasma Sheath over the Capsule]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200101005]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The effects of different high temperature air models on electron density in the plasma sheath of the reentry capsule are studied, including the comparison between chemical non-equilibrium model and thermochemical non-equilibrium model, as well as that between 7 species model and 11 species model. The NND scheme and time preconditioning technique is applied to solve the full Navier-Stokes equations of non-equilibrium flow. Typical results of electron denstiy in the plasma sheath are obtained. The numerical results are good compared with the flight measurement and other numerical results.]]></description>
<pubDate>2013/8/21 9:52:32</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[ZENG Ming,LIU Jun and QU Zhanghua]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>ZENG Ming,LIU Jun and QU Zhanghua</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200101005]]></guid><cfi:id>828</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Analysis of Autonomous Intelligent Control Techniques for Spacecraft and Its Propulsion Systems]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200206001]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[For spacecrafts and its propulsion systems, it is very difficult to apply the classical modern control technology to solve the concerned control problems owing to the complexity of systems, the uncertainty and the unknown of the operating circumstances. The implication, function and construction framework of autonomous intelligent control systems are clarified and discussed. The system architecture of remote agent is analyzed. The reconfiguration of propulsion systems for spacecrafts by autonomous control techniques is also discussed. The analyses and discussion  can be available for reference in the development of autonomous control systems for our spacecrafts in the future.]]></description>
<pubDate>2013/8/21 9:49:42</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[WU Jianjun and LI Hongwei]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>WU Jianjun and LI Hongwei</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200206001]]></guid><cfi:id>827</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Applying AUSMPW+ Scheme to Numerical Simulationof Hypersonic Thermochemical Nonequilibrium Flow]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200206002]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[AUSMPW+ scheme is applied to numerical simulation of hypersonic thermochemical nonequilibrium flow. The third-order MUSCL scheme is used to get more accurate solutions. The present schemes combined with the LU-SGS scheme to improve the efficiency and convergence of computation. Solving axisymmetric Navier-Stokes equations with 11 species air model gets the convergent solutions of thermochemical nonequilibrium flow. The ballistic range experiment is conducted for code validation and the sphere model is made of steel. The computational results are good compared with the experimental data and reference data. Using AUSMPW+ scheme in numerical simulation of hypersonic thermochemical nonequilibrium flow can get the accuracy aerodynamics and the accuracy position of strong bow shock.]]></description>
<pubDate>2013/8/21 9:49:42</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LIU Jun<sup>1</sup>,ZENG Ming<sup>1</sup>,ZHAO Huiyong<sup>2</sup> and LE Jialing<sup>2</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LIU Jun<sup>1</sup>,ZENG Ming<sup>1</sup>,ZHAO Huiyong<sup>2</sup> and LE Jialing<sup>2</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200206002]]></guid><cfi:id>826</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[The Structure and Numerical Experiment of High Order WNND Schemes]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200206003]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Based on the 2nd order NND scheme, a third order WNND scheme was constructed with Jiang and Shu's weighted idea and third order TVD Runge-Kutta method.It was applied in solving linear equation,1D Euler equations and 3D Navier-Stokes equations. The numerical results indicate that WNND scheme brings about less dissipation and spurious oscillations,and it can catch the discontinuities of the flow field.]]></description>
<pubDate>2013/8/21 9:49:42</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[ZHAO Haiyang,LIU Wei and WAN Guoxin]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>ZHAO Haiyang,LIU Wei and WAN Guoxin</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200206003]]></guid><cfi:id>825</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Application of the Spalart-Allmaras Turbulence Model in Hypersonic Aerothermodynamics Computations]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200206004]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Numerical solutions for hypersonic aerothermodynamics of Mar's Pathfinder at Mach number 10 have been computed using the one-equation Spalart-Allmaras turbulence model and the second order MUSCL upwind scheme, AUSM+ scheme combined with LU-SGS implicit iteration has been used here. The numerical results derived from calorically and thermally perfect gas models have been compared with experimental data. Computed heating rates distributions with thermally perfect model are in good agreement with the experiment, however, those in separated zones are poorly predicted. It is seen that thermodynamic properties of hypersonic flows except the separated zones can be correctly simulated with this method if the mesh is appropriately designed, in particular, when the grid resolution near wall is sufficient.]]></description>
<pubDate>2013/8/21 9:49:42</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[XIA Gang,CHENG Wenke and QIN Zizeng]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>XIA Gang,CHENG Wenke and QIN Zizeng</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200206004]]></guid><cfi:id>824</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Numerical Simulation of 3 D Turbulent ReactingFlow in a Solid Ducted Rocket]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200205001]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[During the research on Solid Ducted Rocket (SDR), it is an important link for the design and experiment of SDR that a suitable mathematical model is built to simulate its internal working process. The turbulent reacting model presented in this paper was based on a 3 D ducted rocket. Then the numerical simulation of the model was given and some conclusions were obtained. The conclusions are useful for the design and experiment of the ducted rocket.]]></description>
<pubDate>2013/8/21 9:50:02</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[YU Yong,CHEN Xiaoqian and WANG Zhenguo]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>YU Yong,CHEN Xiaoqian and WANG Zhenguo</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200205001]]></guid><cfi:id>823</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[First Passage Failure-Based Optimization of the Structuresunder Stationary Random Excitation]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200205002]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Optimization and dynamic reliability analysis of the structural system are combined. A methodology of optimum design based total failure probability of the structural system with multi-degree freedom under stationary stochastic excitation is presented when minimum weight of the structure determined by design parameters is the objective function. According to the spectrum analysis theory, the statistical property of the response of structural system under stationary random excitation is analyzed. At the same time, Possion process model based on first passage failure is used to calculate the reliability of the structure, and the optimum design parameters are finally obtained through Hestenes-Powell (HP) method. The result of evaluated examples demonstrates that the method presented in this paper is effective.]]></description>
<pubDate>2013/8/21 9:50:02</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[TIAN Sipeng,REN Junguo and ZHANG Shujun]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>TIAN Sipeng,REN Junguo and ZHANG Shujun</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200205002]]></guid><cfi:id>822</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Effects of Solid Rocket Motor Material Properties on the Structure Integrity]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200205003]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Based on the constitutive relationship of viscoelastic material using the Burgers model and the corresponding viscoelastic finite element method, the finite computational models are established to value the effects of solid rocket motor material parameters on the structure integrity. They include the three-dimension model and the plane strain model. In the case of thermal loading, the three dimension model is necessary, but the plane strain model is accurate enough in the case of internal pressure. Then, the effects of solid rocket motor material parameters on its structure integrity are respectively compared and analyzed under internal pressure and thermal loading by the use of MSC/NASTRAN software system. Under thermal loading, the main factors affecting the motor structure integrity are the propellant Poission's ratio and thermal expansion coefficient. Under the internal pressure, the main factors are the motor liner Poission's ratio, propellant initial elastic modulus and Poission's ratio. These conclusions would be useful for to the design of solid rocket motors.]]></description>
<pubDate>2013/8/21 9:50:02</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[MENG Shangyang,TANG Guojin and LEI Yongjun]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>MENG Shangyang,TANG Guojin and LEI Yongjun</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200205003]]></guid><cfi:id>821</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[The Approximate Simulation for the End Points ofTerminal-sensitive Cluster Warhead]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200205008]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Anti-line target terminal-sensitive cluster warhead is a new kind of bomb.It has good shooting efficiency.Based on the analysis of the scattering and flying properties of the terminal-sensitive cluster warheads，an approximate simulation method for the end points is introduced. Analysis is simple and the result is acceptable. It provides a good referential tool for the analysis of terminal correction cluster warhead system's shooting efficiency.]]></description>
<pubDate>2013/8/21 9:50:02</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[YUAN Tianbao,CHENG Wenke and QIN Zizeng]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>YUAN Tianbao,CHENG Wenke and QIN Zizeng</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200205008]]></guid><cfi:id>820</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Numerical Computation of Radiation Spectrum in Hypersonic Tunnel Thermochemical Nonequilibrium Flowfield]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200204001]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Taking symmetric full Navier-Stokes equations as governing equations, using two temperature and 11 species reacting air model, the hypersonic thermochemical nonequilibrium flow is simulated numerically. Then by using the "line-by-line" radiation model to compute radiation characteristics for the flowfield, the emission and absorption coefficients for 40000 wavelength points in 0.15～2μm are calculated. The radiation spectrum of air mixtrue and the main radiation specie NO in high enthalpy wind tunnel experiments is obtained. The calculation results indicate that vibration temperature exerts important effects on radiation.]]></description>
<pubDate>2013/8/21 9:50:18</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[ZENG Ming,HUANG Hua,LIU Jun and QU Zhanghua]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>ZENG Ming,HUANG Hua,LIU Jun and QU Zhanghua</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200204001]]></guid><cfi:id>819</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Parallel Simulation Studies of Nonlinear Combustion Instabilities in Liquid Rocket Engine]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200204002]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The nonlinear combustion instability process in liquid rocket engine is simulated. The gas controlling Navier-Stokes equations are described under the Euler coordinate.The liquid phase controlling equations are described under the Lagrangian coordinate.The two phase influences of gas and liquid are through the sources of equations.The sequential and parallel codes are written,and the codes are tested in parallel virtual machine environment.The results show that the parallel computation efficiency is reeasonably high.]]></description>
<pubDate>2013/8/21 9:50:18</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[ZHAO Wentao<sup>1</sup>,ZHUANG Fengchen<sup>2</sup> and NIE Wansheng<sup>2</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>ZHAO Wentao<sup>1</sup>,ZHUANG Fengchen<sup>2</sup> and NIE Wansheng<sup>2</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200204002]]></guid><cfi:id>818</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Study of the Unchoked Ducted Rocket Engine and Fuel-Rich Propellant]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200204003]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The operating characteristics of the solid ducted rocket are numerically studied.The results show that the performance of the unchoked ducted rocket (UDR)is superior to that of choked one.The unchoked ducted rocket should work with the high burning-rate-exponent fuel-rich propellant.The aluminum-magnesium fuel-rich propellants for the unchoked ducted rocket with high burning rate,exponent and good flammability limits are developed.Through the connected-pipe tests and numerical analysis,the performance of the unchoked ducted rocket engine is investigated.]]></description>
<pubDate>2013/8/21 9:50:18</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[ZHANG Wei<sup>1</sup>,XIA Zhixun<sup>1</sup>,ZHU Hui<sup>1</sup>,FANG Dingyou<sup>1</sup>,XU Donglai<sup>2</sup>,WANG Hugan<sup>2</sup>,CAO Junwei<sup>2</sup> and ZHU Baohua<sup>2</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>ZHANG Wei<sup>1</sup>,XIA Zhixun<sup>1</sup>,ZHU Hui<sup>1</sup>,FANG Dingyou<sup>1</sup>,XU Donglai<sup>2</sup>,WANG Hugan<sup>2</sup>,CAO Junwei<sup>2</sup> and ZHU Baohua<sup>2</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200204003]]></guid><cfi:id>817</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Multiobjective Distributed Coevolutionary Multidisciplinary Design Optimization]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200204004]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[By introducing multiobjective handling mechanism of nondominated sorting and crowding, ability of distributed coevolutionary multidisciplinary design optimization algorithm is extended to multiobjective multidisciplinary design optimization (MDO) problems. The multiobjective distributed coevolutionary MDO approach maintains sufficient disciplinary autonomy, exploits synergism of disciplinary concurrent design optimizations, meanwhile it obtains a set of well distributed Pareto optimal solutions and makes a good approximation of the whole Pareto optimal front in one single run. It is applied to a missile design optimization problem with two system objectives and three disciplines－aerodynamic, engine, and control. Comparison with the results of the constraint method indicates that the multiobjective coevolutionary MDO approach can effectively approximate Pareto optimal front of the ploblem, providing plenty of information for design decision making.]]></description>
<pubDate>2013/8/21 9:50:18</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[CHEN Qifeng and DAI Jinhai]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>CHEN Qifeng and DAI Jinhai</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200204004]]></guid><cfi:id>816</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Pseudorange Positioning of Two Formation Flying Satellites Using Sphere Coordinate System]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200204005]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[This paper describes the research on the pseudorange positioning of Autonomous Formation Flyer (AFF) of two satellites using pseudolites onboard, which is proposed by the NASA's Space Technology (ST-3). We build model and resolve relative position and time bias between satellites using Cartesian coordinate. The solution error covariance is very grave and unstable because observation geometry is very weak. In order to resolve this problem, we change Cartesian coordinate into sphere coordinate. It can be found that in the sphere coordinate system the solution error covariance is stable and can be used for simulation/covariance analysis.]]></description>
<pubDate>2013/8/21 9:50:18</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[XING Jianjun,XI Xiaoning,WANG Wei and HAN Long]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>XING Jianjun,XI Xiaoning,WANG Wei and HAN Long</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200204005]]></guid><cfi:id>815</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Simulation of Transitional Flow in a 2D Groove by DSMC Method]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200204006]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The transitional fluid flow in a two-dimension groove is simulated by DSMC method. The velocity vector and isotherm are shown at different Knudsen numbers、different span-chord ratios and different temperature wall. The limitation of the DSMC method in simulating the all-velocity flow field is also discussed.]]></description>
<pubDate>2013/8/21 9:50:19</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[WU Xiong,CHEN Weifang and SHI Yuzhong]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>WU Xiong,CHEN Weifang and SHI Yuzhong</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200204006]]></guid><cfi:id>814</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Numerical Simulation of Viscous Flows over ManeuveringMissile with the Control Helm]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200203001]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Under the assumption of perfect gas，the thin layer N-S equations are solved by alternating direction implicit NND scheme，and the space grids of complex wing-shape are generated by solving parabolic partial differential equations. Finally，the numerical simulation results of maneuvering missile with the control helm are shown under the conditions:M<sub>∞</sub>=7.3，α=20°.The results include contours of flow-field, pressure distribution and limiting streamline along the surface.]]></description>
<pubDate>2013/8/21 9:50:35</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LIU Wei]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LIU Wei</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200203001]]></guid><cfi:id>813</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Re-entry Trajectory Design of Inflatable Thermal Shield]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200203002]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The newly developed Inflatable Thermal Shield(ITS) technology offers a simple, reliable and economical way to recover various vehicles from orbits and is therefore possible to be a substitute for parachute systems in the future. The selection of the aeroshell shape for the ITS recovery system is discussed. CFD methods are used to predict the subsonic, transonic and supersonic aerodynamics of the selected shape and compared with the Newtonian hypersonic estimation. The single-stage and two-stage inflation schemes are examined with the calculation of a 90kg cargo's re-entry trajectory, the latter is shown to possess better combination of deceleration and thermal protection and is therefore the ideal ITS re-entry scheme.]]></description>
<pubDate>2013/8/21 9:50:35</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[XIA Gang,CHENG Wenke and QIN Zizeng]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>XIA Gang,CHENG Wenke and QIN Zizeng</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200203002]]></guid><cfi:id>812</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Study of Gas-particle Free Jets with the Particle Simulation Method]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200203003]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[With the particle simulation method employed to trace the trajectory of solid particles and NS equation solved with NND scheme, the gas-particle free jets expanding from a high pressure stagnation chamber through a sonic orfice into a quiescent low pressure chamber is numerically simulated. The results demonstrate that combination of particle simulation method with CFD is an effective approach to the two phases problem.The existence of solid particle is of strong effects on gas flow property.]]></description>
<pubDate>2013/8/21 9:50:35</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[HUANG Lin and LIU Jun]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>HUANG Lin and LIU Jun</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200203003]]></guid><cfi:id>811</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Assessment of Aerodynamic Derivatives of the Ideal Flat PlateBased on the Moving Grid Method]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200203004]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Numerical simulation of the flow field around the oscillating ideal flat plate is presented  to assess the aerodynamic derivatives. The time-dependent  incompressible Navier-Stokes equations are decoupled using Projection-2 method. The second order semi-implicit scheme is employed in temporal and spatial discretization for the momentum equations of intermediate velocities, while the Possion's equation for pressure is solved efficiently by using the multigrids method. Unsteady aerodynamic force on the heaving or pitching oscillated flat plate are computed and the motion of the plate is accounted by the moving grid method. The aerodynamic derivatives are extracted with the Least Square Method. The computed aerodynamic derivatives are in better agreement with Theodorsen's theoretic solutions.]]></description>
<pubDate>2013/8/21 9:50:35</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[ZHU Zhiwen<sup>1</sup>,CHEN Zhengqing<sup>1</sup> and CHEN Weifang<sup>2</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>ZHU Zhiwen<sup>1</sup>,CHEN Zhengqing<sup>1</sup> and CHEN Weifang<sup>2</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200203004]]></guid><cfi:id>810</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[The Factors Influencing the Synthetic Jet]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200203008]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Based on integrating a great deal of foreign experimental data and numerical simulation data, the driving factors and configuration factors influencing characters of the synthetic jet are analyzed and summarized. Then the influences of Re and St for synthetic jet are investigated with numerical simulation method. And a correlation function reflecting the characters of synthetic jet actuator is obtained It provides references for the actuator preliminary design.]]></description>
<pubDate>2013/8/21 9:50:35</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LUO Zhenbing,XIA Zhixun,FANG Dingyou,WANG Zhiji and HU Jianxin]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LUO Zhenbing,XIA Zhixun,FANG Dingyou,WANG Zhiji and HU Jianxin</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200203008]]></guid><cfi:id>809</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Three-Axis Magnetometer Orbit Determination]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200203021]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Satellite tends to be microminiaturization in the future. It needs to adopt a small, cheap and middle precision autonomous navigation system. According to the measurements of three-axis magnetometer in the body frame, the parameters of the orbit can be determined by using of Kalman Filter.The result of simulation shows that orbit determination by dint of three-axis magnetometer is of medium precision, which can satisfy some requirments of orbit determination.]]></description>
<pubDate>2013/8/21 9:50:36</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[WU Meiping,TIAN Jing and HU Xiaoping]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>WU Meiping,TIAN Jing and HU Xiaoping</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200203021]]></guid><cfi:id>808</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Nonprobabilistic Convex Set Theoretic Models for StructuralAnalysis of Solid Propellant Grain]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200202001]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The uncertainty of parameters may greatly affect structural analysis of solid propellant grain. Nonpropabilistic convex set theoretic models, combining viscoelastic finite element method, are developed to study the uncertainty of structures. Incremental method is applied to solving the hereditary integrals. Perturbation method is used to predict the variability of structural response. The developed method is suitable for uncertain structural analysis of solid propellant grain. By comparing with stochastic structural analysis, relations between the two methods have been found.]]></description>
<pubDate>2013/8/21 9:50:52</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[ZHANG Hailian and ZHOU Jianping]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>ZHANG Hailian and ZHOU Jianping</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200202001]]></guid><cfi:id>807</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Satellite Formation Flying with J<sub>2</sub> Perturbation]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200202002]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[As to the formation flying with the reference satellite running on the circle orbit, the J<sub>2</sub> effect is analyzed. On this basis, a method is presented, which can greatly mitigate the breakage of the J<sub>2</sub> term by adjusting the semi-major axis of the flying-around satellite. Furthermore,the cost required for formation-keeping is evaluated under impulse assumption. Numerical results show that satellite formations with semi-major axis adjustments will last much longer, and save much more fuel.]]></description>
<pubDate>2013/8/21 9:50:52</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[ZHANG Yukun and DAI Jinhai]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>ZHANG Yukun and DAI Jinhai</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200202002]]></guid><cfi:id>806</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Calculation of Cosmic High Energy Proton Induced Single Event Upset Rate]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200202003]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[By simplifying the sensible volume of semiconductor devices, the energy deposited by the cosmic high-energy protons in the sensible volume of semiconductor devices is calculated. Then by using the Weibull function derived by the ground heavy ion SEU experiments, the SEU rates of several devices by the shielding of 33 mm Aluminum in the CRRRES satellite orbit are calculated. The results are compared and analyzed.]]></description>
<pubDate>2013/8/21 9:50:52</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[WANG Tongquan,DAI Hongyi,SHEN Yongping,ZHANG Ruoqi and XIAO Yabin]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>WANG Tongquan,DAI Hongyi,SHEN Yongping,ZHANG Ruoqi and XIAO Yabin</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200202003]]></guid><cfi:id>805</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Experimental Study on Mechanical Properties of 1420cs Al-Li Alloy Moulding Material]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200202004]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The stress-ongitudinal strain curves are tested using electrical measuring technique. The relations of transverse strain and longitudinal strain are also examined. Some properties such as σ<sub>0.2</sub>，σ<sub>b</sub>,E and μ are derived. Testing results  indicate that transverse strain has distinct jumpiness when stress exceeds proportional elongation point. The properties of the material are different from others.The fracture toughness of surface crack is also tested.]]></description>
<pubDate>2013/8/21 9:50:52</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[SONG Xiancun and LEI Yongjun]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>SONG Xiancun and LEI Yongjun</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200202004]]></guid><cfi:id>804</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Propositional Logic-based Method of LiquidRocket Engine Fault Diagnosis]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200201001]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[To provide an efficient way easy to express and organize the fault knowledge of liquid rocket engine, a qualitative model is first founded by the qualitative description of the observation and characteristic of the system in the form of propositional logic formulae and clauses, then fault diagnosis is continued based on the inference rules of resolution step and modus ponens, and diagnosis results with test data manifest that the provided method has better ability.]]></description>
<pubDate>2013/8/21 9:51:06</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LIU Honggang,WU Jianjun and CHEN Qizhi]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LIU Honggang,WU Jianjun and CHEN Qizhi</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200201001]]></guid><cfi:id>803</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Fuzzy Control in Changing Conditions forStaged Combustion Cycle Engine]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200201002]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[A fuzzy control is studied, which is used for the feedback control in the changing condition process of the staged combustion cycle liquid rocket engine. Simulation research has shown that the fuzzy sliding mode control surpasses usual variable structure control in weakening chattering.]]></description>
<pubDate>2013/8/21 9:51:06</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[HUANG Minchao and LIU Kun]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>HUANG Minchao and LIU Kun</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200201002]]></guid><cfi:id>802</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[The Selection of the Stage Number for the Reusable LaunchingVehicle Program Based on Life-Cycle-Cost Analysis]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200201003]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The launching cost model of reusable launching vehicle based on Life-Cycle-Cost(LCC) analysis is presented. The LCC of various reusable launching vehicle programs with different stages are calculated by applying the newly built analysis model. Components of the LCC are presented specially, and the relationship between each of the components of the LCC and stage number is also analyzed. The result indicates that the LCC of Two-Stage-to-Orbit (TSTO) reusable launching vehicle program is the lowest, so TSTO reusable launching vehicle program is the relatively optimal selection based on the present developing level.]]></description>
<pubDate>2013/8/21 9:51:06</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LUO Shibin,LUO Wencai,ZHANG Hailian and WANG Zhenguo]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LUO Shibin,LUO Wencai,ZHANG Hailian and WANG Zhenguo</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200201003]]></guid><cfi:id>801</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Transient Characteristics During Pulse Operation ofLiquid Feed Line for the Attitude Control Rocket Engine]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200201004]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[By means of the finite difference scheme of characteristic method, the transient flows are simulated for the attitude control propulsion subsystem during the pulse operation. The effect of different conditions on dynamic behavior in pulse mode is investigated. The results are agreeable with the test process. The method can be used to analyze the dynamic performance of complex propulsion system consisting of numerous pipes, valves and thrusters. The results are valuable for designers.]]></description>
<pubDate>2013/8/21 9:51:06</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[NIE Wansheng<sup>1</sup>,CHEN Xinhua<sup>1</sup>,ZHAO Wentao<sup>2</sup> and ZHUANG Fengchen<sup>1</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>NIE Wansheng<sup>1</sup>,CHEN Xinhua<sup>1</sup>,ZHAO Wentao<sup>2</sup> and ZHUANG Fengchen<sup>1</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200201004]]></guid><cfi:id>800</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Numerical Simulatiom of the Shock Train Structurein the Supersonic Diffuser]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200201005]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Complicated flow field of shock/boundary layer interaction in the supersonic diffuser is simulated by solving the Reynolds-averaged Navier-stokes equations in 2D,axisymmetric and 3D cases. The length of shock train, the distance of each shocks in it and the level of pressure recovered are compared with each case. Also, the oscillation phenomenon of the shock train is captured through Runge-Kutta method when the freestream mach number is 3 and the results are compared with experimental data.]]></description>
<pubDate>2013/8/21 9:51:06</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LI Hua,FAN Xiaoqiang and DING Meng]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LI Hua,FAN Xiaoqiang and DING Meng</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200201005]]></guid><cfi:id>799</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Buckling Analysis of Cylindrical Shell Based onMixed Variables Transfer Function Method]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200201006]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[A mixed variables transfer function is presented for analyzing the stability  of orthotropic cylindrical shells and stepped cylindrical shells. First, displacement variables are expanded in trigonometric series of circumferential coordinate. Flügge thin shell theory and variational principle are adopted to obtain governing equations and  find dual force variables. Consequently, governing equations are written in the form of mixed variables. State-space equation of the system is established by defining mixed state variables. Then, by transfer function method, closed-formed solutions for buckling problems of cylindrical shells under axial compression with arbitrary axisymmetric boundary conditions are obtained. Finally, solutions for buckling problems of stepped cylindrical shells are obtained by enforcing displacement continuity and force balance. Driving process of analytical solutions show that it is very convenient for introducing boundary conditions and solving the buckling problems of stepped cylindrical shells in this method. Numerical results validate this method.]]></description>
<pubDate>2013/8/21 9:51:06</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LI Daokui,ZHOU Jianping and LEI Yongjun]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LI Daokui,ZHOU Jianping and LEI Yongjun</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200201006]]></guid><cfi:id>798</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Relative States Determination for Formation Satellite Constellation by Using Pseudo-ranging Between Satellites]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200201007]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In the case of the formation flying constellation, this paper discusses some problems about the determination of relative states, which includes the relative position, attitude and time between the formation flying satellites, by using precise pseudo-ranging. The problems are the selection of coordinate system and independent state parameters, the setting of observation equations, conversion of constellation's states, orientation and installing of antenna. Numerical simulation and analysis are made for an earth-observation constellation.]]></description>
<pubDate>2013/8/21 9:51:07</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[WANG Wei,XI Xiaoning and HAN Long]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>WANG Wei,XI Xiaoning and HAN Long</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200201007]]></guid><cfi:id>797</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[The Bending Solution of Anisotropic ThinPlate Acted with Arbitrary Loading]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200201008]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Composite material plate usually is anisotropic plate, To solve the bending problem for plate, trigonometric series solution in complex number form and double sine series solution are used to establish a general solution of differential equation for anisotropic thin plates in bending problem. It can be used to solve bending problem for arbitrary loading with whatever boundaries. As an example a square plate with four edges fixed has been calculated. The result agrees with that in literature. This common analytical method is simple and complete, and easy to use in practice.]]></description>
<pubDate>2013/8/21 9:51:07</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[HUANG Yan,LIAO Ying and QIU Zhongsheng]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>HUANG Yan,LIAO Ying and QIU Zhongsheng</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200201008]]></guid><cfi:id>796</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[μ-Synthesis Research on MAV Flight Controller Design]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200305001]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[From Micro Air Vehicle (MAV) flight control system's basic constitution, this paper discusses MAV flight controller's performance criteria, robustness criteria, security criteria and control energy criteria. The linear model approach is presented based on MAV parametric uncertainty such as  mass, span, length of fuselage, placement of mass, flight velocity, and aerodynamic compute errors. The MAV flight controller's Δ-P-K architecture is built, and generalized plant transfer function matrix obtained. And further more, we discusses the μ-synthesis approach by which MAV flight controller is designed.]]></description>
<pubDate>2013/6/14 9:08:38</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[ZENG Qinghua and ZHANG WeiHua]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>ZENG Qinghua and ZHANG WeiHua</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200305001]]></guid><cfi:id>795</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[The Attitude Control of Spacecraft with Large Flexible Solar Array]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200305002]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[A simple and efficient method PDA is put forward, which can suppress deformation vibration of the solar battery array. The attitude rigid acceleration feedback is combined with the classic PD method used usually in the aerospace engineering. The method has been demonstrated to be efficient in suppression of vibration for the attitude maneuver and keeping by virtue of numerical simulation and experiment. Certain applications may be made to the rendezvous and dock engineering or orbital maneuvour .]]></description>
<pubDate>2013/6/14 9:08:38</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LIU Xinjian,LEI Yongjun and TANG Qiangang]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LIU Xinjian,LEI Yongjun and TANG Qiangang</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200305002]]></guid><cfi:id>794</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Optimal Finite-Thrust Rendezvous Using Nonlinear Programming]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200305003]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Spacecraft optimal rendezvous is studied using nonlinear programming method. A recently developed direct optimization technique is  employed, which uses a piecewise polynomial representation for the state and controls, thus converting the optimal control problem into a nonlinear programming one. When using the method, the whole orbit is separated to thrust arcs and non-thrust arcs, then the collocation method is used to produce the constraints of thrust arcs, and state transition matrix is applied to producing the constraints of non-thrust arcs. At last, the simulation of coplanar rendezvous verifies the effectiveness and robustness of the method.]]></description>
<pubDate>2013/6/14 9:08:38</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[WANG Hua and TANG Guojin]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>WANG Hua and TANG Guojin</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200305003]]></guid><cfi:id>793</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Three-Dimensional Numerical Simulation of Hypersonic Flowfieldwith Lateral Jet]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200305004]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The interaction flow with lateral jet in hypersonic flowfield was simulated numerically by solving three dimensional full N-S equations, using finite volume method, half implied Harten-TVD scheme and a algebraic Baldwin-Lomax model. The computation result was compared with the test data  from foreign articles. The simulation captured the structures of shockwaves and eddies near the jet clearly, and showed the disturbed region to the missile. It proves that the jet has deep influence on the missile.]]></description>
<pubDate>2013/6/14 0:00:00</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[TIAN Zhengyu,FAN Xiaoqiang and LI Hua]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>TIAN Zhengyu,FAN Xiaoqiang and LI Hua</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200305004]]></guid><cfi:id>792</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[The Analysis of the Compensation Effect of Yaw Steering for SAR]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200305005]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[A“Satellite-Earth-Target”geometric model is presented, and the exact Doppler centroid is obtained. On the basis of the simplified model, the yaw steering is found. From the analysis of the two models, a conclusion about the yaw steering's compensation effect is drawn.]]></description>
<pubDate>2013/6/14 9:08:38</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[MENG Yunhe,YIN Qiuyan and DAI Jinhai]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>MENG Yunhe,YIN Qiuyan and DAI Jinhai</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200305005]]></guid><cfi:id>791</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Identification of Flutter Derivatives of Long-Span BridgeSection-Model from Forced Vibration Datas]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200305006]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[A 2-D forced-vibration driver for ADs identification of long-span bridge section-model has been developed, by which the section-model is forced to perform 1-D or coupled torsional/vertical sinusoidal motion. In each test, lift force and torsional moment are both measured by force balances, the motions of the model are measured by accelerators, then the eight ADs are obtained by a hybrid method of spectrum analysis and non-linear optimization. The results of a flat plate sectional model obtained in wind tunnel tests by this driver are compared with the solutions of Theodorson flat plate and other published datas,the comparison shows that all of the datas share the same trends.]]></description>
<pubDate>2013/6/14 9:08:38</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[CHENG Zhongyu<sup>1</sup>,ZhANG qi<sup>1</sup>,CHEN Zhengqing<sup>2</sup> and YU Xiangdong<sup>2</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>CHENG Zhongyu<sup>1</sup>,ZhANG qi<sup>1</sup>,CHEN Zhengqing<sup>2</sup> and YU Xiangdong<sup>2</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200305006]]></guid><cfi:id>790</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[High Frequency Combustion Instabilities inLiquid Rocket Engine Based on Nonlinear Dynamics]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200304001]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The nonlinear high frequency combustion instability process in the liquid rocket engine is simulated with the method of nonlinear dynamics. The gas controlling Navier-Stokes equations are described under the Euler coordinate. The liquid phase controlling equations are described under the Lagrangian coordinate. The two-phase interactions of the gas and liquid are coupled through the sources of equations. The spray process in the rocket engine is described with the theory of high pressure evaporation. The two phase turbulent combustion steady process and high combustion instability in the liquid rocket engine are simulated with the method of computational combustion dynamics. The conclusion is drawn that the high frequency combustion instability in the liquid rocket engine is similar to the strange attractor which looks like Lorenz attractor.]]></description>
<pubDate>2013/6/14 9:08:25</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[ZHAO Wentao<sup>1</sup> and ZHUANG Fengchen<sup>2</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>ZHAO Wentao<sup>1</sup> and ZHUANG Fengchen<sup>2</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200304001]]></guid><cfi:id>789</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Numerical Simulation of Temperature Field in the Two-layeredShell Irradiated by the Intensive Laser Beam]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200304002]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The temperature field distribution in the two-layered shell is simulated numerically by using the finite element method. The influence of material properties of the outer shell on the temperature rise in the inner shell is analyzed under a given laser power. The results indicate that the difference of material properties of the outer shell in specific, thermal conductivity as well as its thickness can greatly change the temperature of the inner shell. The thermal wastage in the inner shell between the inner and outer shell are investigated in the process of computation. Moreover, the effect of temperature-depending material properties of the inner shell on its temperature rise is presented. And some significant conclusions are reached by comparing with the temperature field distribution of the one-layered shell irradiated by the intensive laser beam.]]></description>
<pubDate>2013/6/14 9:08:25</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[WU Fei,ZHOU Jianping and LEI Yongjun]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>WU Fei,ZHOU Jianping and LEI Yongjun</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200304002]]></guid><cfi:id>788</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Analysis of the Sensitivity of Hypersonic Cruise Vehicle Airframe/Propulsion System Integrated Design Parameters]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200304003]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[An airframe/propulsion system integrated design of hypersonic cruise vehicle overall performance analysis model is set up. The parameter sensitivity of the hypersonic cruise vehicle airframe/propulsion system integrated design is discussed. A new design parameters sensitivity analytical method and a new design parameters region classifying method are presented. Based on the vehicle performance analysis, influence degrees of the design parameters are obtained, and the changing region of design parameters is classified.]]></description>
<pubDate>2013/6/14 9:08:25</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LUO Shibin,LUO Wencai and WANG Zhenguo]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LUO Shibin,LUO Wencai and WANG Zhenguo</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200304003]]></guid><cfi:id>787</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Numerical Solution of the Aerodynamic Properties ofthe Rotating Projectiles]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200304004]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[To improve the precision of the aerodynamic coefficients of the projectiles during calculating trajectories and designing projectiles, the drag, lift, pitching moment, roll damping moment, Magnus force and moment of the projectiles are computed by solving N-S equations applying an implicit LU scheme, and considering an algebraic turbulence model and the boundary condition for rotating body surface. It is indicated that the aerodynamic coefficients of the rotating projectiles obtained by means of the numerical simulation are better than those previously obtained by means of the engineering estimate by the comparison of the computing results and the experimental results of the T388 shell, and by the ballistic calculations of a certain howitzer projectile using the aerodynamic coefficients obtained with this technique.]]></description>
<pubDate>2013/6/14 9:08:25</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[WANG Zhijie<sup>1</sup>,CHEN Weifang<sup>2</sup> and LI Jie<sup>2</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>WANG Zhijie<sup>1</sup>,CHEN Weifang<sup>2</sup> and LI Jie<sup>2</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200304004]]></guid><cfi:id>786</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[The Effects of Second-flow on the Vacuum-degree ofAnnular Supersonic Air Ejector]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200303002]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The time-dependent method of the computational fluid dynamics is applied to solving the 2-dimensional axisymmetric Navier-Stokes equations, and the flowfields of the 2-dimensional axisymmetric annular supersonic air-ejectors are simulated. Based on the previous work, the balance mechanism of the blind-cavity is considered and the effect of the second-flow on the ejected vacuum is discussed. It's found that the existence of second-flow has an important effect on the flowfield structure of the ejector, and that in comparison with the zero-second-flow condition, a little of the second-flow will reduce the ejector vacuum remarkably.]]></description>
<pubDate>2013/6/14 9:08:13</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[XU Wanwu,TAN Jianguo and WANG Zhenguo]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>XU Wanwu,TAN Jianguo and WANG Zhenguo</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200303002]]></guid><cfi:id>785</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Laser Induced Fluorescence Technology for Measurements of OHDistribution in Flames]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200303003]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[OH radical distribution images were obtained with planar laser induced fluorescence (PLIF) in several different flames. The principle of measurement was clarified briefly. Factors that influence the measurements were discussed. The PLIF images were com-pared with the  spontaneous emission image of the flame. Application of PLIF technology to combustion process analysis was attempted. Results support the viewpoint that this technology is a powerful tool for the combustion diagnosis.]]></description>
<pubDate>2013/6/14 9:08:13</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LI Mailiang,ZHOU Jin,GENG Hui and WANG Zhenguo]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LI Mailiang,ZHOU Jin,GENG Hui and WANG Zhenguo</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200303003]]></guid><cfi:id>784</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Researches on Wavelet-based Vibration Control of LargeSpace Smart Structures]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200303004]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Based on the optimal control theory, an active vibration control method of smart structures has been researched. In this research, the scaling function transformation of the wavelets has been adopted; sensors and actuators are also designed. Finally some largespacetrussstructures have been taken as illustrated examples, and some digital simulations have been made. The numerical results show that the control method is effective.]]></description>
<pubDate>2013/6/14 0:00:00</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[SI Hongwei and LI Dongxu]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>SI Hongwei and LI Dongxu</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200303004]]></guid><cfi:id>783</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Accelerated Aging and Life Forecast of Solid Rocket Motorwith Bonded Interface]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200303008]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Aging test of bonded interface in solid rocket motor is discussed. The appropriate mathematical model is established according to the variance of its mechanical properties. Storage life is estimated using this model.]]></description>
<pubDate>2013/6/14 0:00:00</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[SONG  Xiancun]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>SONG  Xiancun</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200303008]]></guid><cfi:id>782</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Parellel Numerical Simulation of the Three-dimensional Flow Fieldaround the Hypersonic Waverider Shape Vehicle]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200302002]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Based on the distributed parellel computing platform with the LINUX+MPI parellel environment, a parellel numerical computing method with finite volume method(FVM), OC-TVD scheme, B-L turbulence model and domain decomposition method was developed to solve the 3-D compressible Reynolds-averaged N-S equations. This method was used to simulate the flow field of the hypersonic waverider shape vehicle. The numerical results indicate that the shock across the zone boundary is continuous and the parellel speedup ratio reachs 6.8 when 8 cpu is in using.]]></description>
<pubDate>2013/6/14 9:08:02</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[FAN Xiaoqiang,LI Hua,LI Xiaoyu and TIAN Zhengyu]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>FAN Xiaoqiang,LI Hua,LI Xiaoyu and TIAN Zhengyu</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200302002]]></guid><cfi:id>781</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Optimal Analysis of Tripropellant Engine for SSTO]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200302003]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The trajectory model and the mass model of SSTO reusable vehicle and the performance model of tripropellant liquid rocket engine are established. Optimal analysis whose objective is minimizing the vehicle gross mass is performed to attain the engine parameters. Results show that the performance of tripropellant engine is 10% higher than that of LH/LOX engine. This research is the basis of design and analysis of tripropellant propulsion system.]]></description>
<pubDate>2013/6/14 9:08:02</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[TAN Jianguo,XU Wanwu and WANG Zhenguo]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>TAN Jianguo,XU Wanwu and WANG Zhenguo</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200302003]]></guid><cfi:id>780</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Multimethod Collaborative Optimization Algorithm Applied to IntegralOptimal Design of Missile Propelled by Unchoked Solid Rocket Ramjet]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200302004]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The performance of the solid rocket ramjet and missile influence each other greatly. Integral system project design of missile propelled by unchoked solid rocket ramjet can bring the performance of the solid rocket ramjet and missile into play and make them work in harmony，and improve the performance of the  missile and ramjet. Multimethod collaborative optimization algorithm based on genetic algorithm、Powell method and pattern searching method is used to find the best parameters of the system project of the missile propelled by the unchoked rocket ramjet. Using the optimized parameters, the missile can get better system performance.]]></description>
<pubDate>2013/6/14 9:08:02</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LUO Wencai,LUO Shibin and WANG Zhenguo]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LUO Wencai,LUO Shibin and WANG Zhenguo</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200302004]]></guid><cfi:id>779</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[The Bayes Method for Rocket Engine Reliability Growth Evaluation]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200302006]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[During the development of the rocket engine, the new engine is coming from the fault analysis and the removal of its predecessors. In this paper, the concept of equivalent test data is presented. Then, using the Bayesian method, with a few field test examples, the reliability of new products are evaluated. With the result of the stage reliability evaluation, the reliability growth of the system can be evaluated. A sample is given to illustrate the method.]]></description>
<pubDate>2013/6/14 9:08:02</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LIU Qi,FENG Jing and ZHOU Jinglun]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LIU Qi,FENG Jing and ZHOU Jinglun</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200302006]]></guid><cfi:id>778</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Analysis of the Key Technology and Construction of Ion Thruster]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200301002]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The fundamental principle and construction of ion thruster are introduced. The operating principle and characteristics of the main components and subsystems of ion thruster, including the ion optic system, hollow cathode, ionization chamber, neutralizer etc. are analyzed and discussed. The development trend of ion thruster and its key technology is indicated.]]></description>
<pubDate>2013/6/14 9:07:49</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[WU Jianjun and ZHANG Chuansheng]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>WU Jianjun and ZHANG Chuansheng</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200301002]]></guid><cfi:id>777</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Semi-analytic Model for Modal Characteristics ofCombined Panels of Solar Array]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200301003]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Based on the theory of transfer function method of distributed parameter system, a semi-analytic model of structural dynamic characteristics for solar array is established. In this model, the solar panel is divided into some strip elements, and the joint hinge on solar array is simplified as a uniform beam element, and the strip element and the beam element are combined by displacement continuum and force equilibrium at their common nodes. Numerical results of modal characteristics for single and composed panels of certain satellite solar array are presented, and these results are compared with those of finite element method.]]></description>
<pubDate>2013/6/14 9:07:49</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LEI Yongjun,LI Dongxu and TANG Guojin]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LEI Yongjun,LI Dongxu and TANG Guojin</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200301003]]></guid><cfi:id>776</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Analysis and Improvement of High Precision, HighResolution WENO Schemes]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200301004]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[High precision,high resolution schemes have significant means in raising the level of the complex supersonic flowfield calculation. WENO schemes are new schemes recently developed which are based on the ENO schemes. The algorithm of weighted factors in WENO schemes was studied and analyzed by theoretic and numeric method. Then, the improvement of algorithm was given. Through applying the improved algorithm to two model problems, it shows that the weighted factor of improved schemes is more smooth. The improve schemes preserve high precision, high resolution characteristics and solve the problem of week oscillatory with varied mesh.]]></description>
<pubDate>2013/6/14 9:07:49</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[HOU Zhongxi,YI Shihe and LI Hua]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>HOU Zhongxi,YI Shihe and LI Hua</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200301004]]></guid><cfi:id>775</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Numerical Simulation of Coupled Aeroheating and Solid HeatPenetration for a Hypersonic Blunt Body]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200301008]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The coupling problems of aeroheating and solid heat penetration are very important to aerospace and engineering applications. The loosely-coupled and the fully-coupled methodology are both applied to simulate a two-dimensional hypersonic fluid-solid thermally coupled flow around a cylinder. The unsteady Navier-Stokes equations and the 2D unsteady heat-conduction equation are derived, solved by the finite volume and the Galerkin finite element methods respectively. The coupling is processed by the boundary conditions of heat flux and temperature at the fluid/solid interface. The flow part is solved by AUSM+ and explicit multi-step Runge-Kutta method. The results are compared with the experimental data and computational results from the reference.  The method is shown to give good predictions of the temperature variation and heat flux distribution, and the loosely-coupled method is shown to be more efficient and similar accurate if the characteristic time for fluid is far less than the time for solid.]]></description>
<pubDate>2013/6/14 9:07:49</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[XIA Gang,LIU Xinjian,CHENG Wenke and QIN Zizeng]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>XIA Gang,LIU Xinjian,CHENG Wenke and QIN Zizeng</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200301008]]></guid><cfi:id>774</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Design of the Evaluation System for Air-to-air Attack of Fighters]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200301009]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In view of an evaluation system for the air-to-air attack of fighters, the scheme, functions and key technology of this system are described. The development of the evaluation system for air combat in the future is analyzed. Some block diagram for the framework are given in this paper.]]></description>
<pubDate>2013/6/14 9:07:49</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[YANG  Leping]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>YANG  Leping</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200301009]]></guid><cfi:id>773</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[The Numerical Analysis of Oscillatory Characteristics in 3DSupersonic Open Cavity]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200406001]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The unsteady oscillatory characteristics in supersonic cavity are numerically studied in the steady inflow condition. 5 order WENO scheme and 3 order Runge-Kutta algorithm are used. Through numerically calculating and analyzing the pressure changing procedure, sound pressure level, oscillatory frequency in 2D and 3D cavity, it shows that there is typical pressure oscillatory in cavity. The oscillatory has approximate cycle, but the law of cycle is very complex. 3D cavity exerts little effect on the main oscillatory frequency, but the oscillatory intensity is quite different in 2D and 3D.]]></description>
<pubDate>2013/5/8 10:45:33</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[HOU Zhongxi,XIA Gang and QIN Zizeng]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>HOU Zhongxi,XIA Gang and QIN Zizeng</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200406001]]></guid><cfi:id>772</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Numerical Study of Ignition Transient in Large AspectRatio Solid Rocket Motor]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200406002]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Using N-S equations to describe the ignition transient model of the large aspect ratio solid rocket motor, this model includes the igniter and burning room and nozzle. Comparing the calculation and experiment shows the correction of it. Furthermore, there are vibration and rapping during the ignition transient besides rapid pressure rising.]]></description>
<pubDate>2013/5/8 10:45:33</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[ZHONG Tao,ZHANG Weihua and WANG Zhongwei]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>ZHONG Tao,ZHANG Weihua and WANG Zhongwei</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200406002]]></guid><cfi:id>771</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Experimental Study of the Effects of the Geometric Parameters ofActuator on Synthetic Jets]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200406003]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[For the purpose of designing a high performance synthetic jet actuator, the performance of actuators has been investigated experimentally for a range of geometric parameters. It is showed that the performance of a synthetic jet actuator is determined by these geometric parameters, the square/rectangle exit-slot is propitious to found a powerful synthetic jet, and the maximal velocity of actuator with dual-membranes is doubled compared with the actuator with a single-membrane. It is also found that varying the pressing states of membrane does not change the main relations between synthetic jets and the exciting frequency but affects the synthetic jet velocity values a lot.]]></description>
<pubDate>2013/5/8 10:45:33</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LUO Zhenbing,ZHU Bopeng,XIA Zhixun and WANG Dequan]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LUO Zhenbing,ZHU Bopeng,XIA Zhixun and WANG Dequan</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200406003]]></guid><cfi:id>770</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[The Effect of Wall Injection of Teflon Ablating Material onElectron Number Density]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200406007]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The chemical non-equilibrium flows over a teflon ablative wall are calculated numerically by solving NS equations with pure-air and teflon-air chemical reaction system. The overall teflon-air chemical system used consists of 19 species and 28 reactions. The effect of wall injection of teflon ablating material on electron number density are discussed.]]></description>
<pubDate>2013/5/8 10:45:33</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[SHI Yuzhong,WANG Maoyan,YIN Le and CHEN Weifang]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>SHI Yuzhong,WANG Maoyan,YIN Le and CHEN Weifang</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200406007]]></guid><cfi:id>769</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Calculation of Bookbinding Parameters and Integrating Method of theSoftware of Liquid Propellant Utilizing System]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200406018]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[A calculating method of bookbinding parameters of the liquid propellant utilizing system is designed, and the integrating method is studied of the distributed computation based on CORBA. It is proved practical in the software project and can meet the need of the distributed computation.]]></description>
<pubDate>2013/5/8 10:45:34</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[YAN Xiaoqing,LI Ziran and ZHOU Jin]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>YAN Xiaoqing,LI Ziran and ZHOU Jin</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200406018]]></guid><cfi:id>768</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Incremental Interface Element Method of Viscoelastic Materials]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200405001]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Formulas of the incremental interface element method for viscoelastic materials are deduced in the interface element model. The numeral example shows that the viscoelastic interface element method is effective in the analysis of viscoelastic discontinuousness medium.]]></description>
<pubDate>2013/5/3 9:19:51</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LIU Fu,REN Junguo and ZHOU Jianping]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LIU Fu,REN Junguo and ZHOU Jianping</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200405001]]></guid><cfi:id>767</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[The Modeling of the Working Characteristics andSimulation of the Flying Performance of Helicopters]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200405002]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The modeling & simulation of the flying performance of helicopters is developed here in order to maintain them based on their states. It is centered on the modeling of the working characteristics of the turboshaft. First, the descriptions of the flying performance of helicopters and the characteristics of the turboshaft are discussed, and a math model of the working process of the turboshaft is built. Then the model is predigested according to the calculating program of the engine's test performance. Finally, the flying performance simulation is realized through the calculation based on the simplified model. The results show that this method is credible and high efficienct.]]></description>
<pubDate>2013/5/3 9:19:52</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LIAO Ying<sup>1</sup>,ZHUANG Jingzhao<sup>2</sup> and LIANG Jiahong<sup>3</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LIAO Ying<sup>1</sup>,ZHUANG Jingzhao<sup>2</sup> and LIANG Jiahong<sup>3</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200405002]]></guid><cfi:id>766</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Simulation of Micro-Nozzle Flow by DSMC Method]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200405003]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[At present, micro-spacecrafts are being developed. Micro-nozzles are very important in propulsion systems of micro-spacecrafts. So further study on micro-nozzles is essential. DSMC(direct simulation Monte-Carlo)calculations for the flow in axisymmetric micro-nozzles are conducted on molecular-based models. The influence of the mass flow rate and dimension on the flow and performance in the nozzle are also discussed. The study indicates that the mass flow rate and dimension of the nozzle have different degrees of influence on the flow and performance.]]></description>
<pubDate>2013/5/3 9:19:52</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[YIN Le,CHEN Weifang and SHI Yuzhong]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>YIN Le,CHEN Weifang and SHI Yuzhong</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200405003]]></guid><cfi:id>765</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[The Progress of the Research on the Micro AirVehicle's Flight Control]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200405008]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The micro air vehicle is a growing field of new aircraft and its control is a challenging key technology in the MAV research. Summarizing MAV, this paper presents a survey of the current situation and development of MAV flight controller, and analyzes some key tech problems in the design of  MAV flight controller, which includes the scheme of flight control, on-board sensors, new control device, flight control algorithms, and controller design methods.]]></description>
<pubDate>2013/5/3 9:19:52</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[ZHANG Weihua and ZENG Qinghua]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>ZHANG Weihua and ZENG Qinghua</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200405008]]></guid><cfi:id>764</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[A Bayesian Learning Algorithm Based on Search-Coding Method]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200405014]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Naǐve-Bayes algorithm is a stable supervised learning method, and it is difficult to improve its predicting accuracy. This paper analyzes the properties of the error-correcting output codes generated by search-coding method at first, then presents a search coding based on vaǐve Bayes algorithm (SCNB), and describes the flow chart of SCNB in detail. Experimental results show that search-coding method is an efficient approach to improve the generalization for Bayesian classifiers.]]></description>
<pubDate>2013/5/3 9:19:52</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[JIANG Yanhuang and YANG Xuejun]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>JIANG Yanhuang and YANG Xuejun</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200405014]]></guid><cfi:id>763</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[ViCowel: A Scalable Wavelet Based Video Coding Approach forVideo Multicast Applications]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200405016]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[WebLearning-plus is a multicast-based collaborative learning environment we developed, in which scalable video coding and adaptive multicast transmission are the key issues. According to the demand of adaptive video multicast in WebLearning-plus for the coder, we present a new scalable wavelet based video coding approach named ViCowel, which is a kind of set partition based on line scanning. Experiments show that it has better flexibility in video multicast applications.]]></description>
<pubDate>2013/5/3 9:19:52</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[ZHANG Jun,LIU Wei,WANG Hui and LI Guohui]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>ZHANG Jun,LIU Wei,WANG Hui and LI Guohui</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200405016]]></guid><cfi:id>762</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[The Design and Realization of Hierarchical Framework ofNews Video Process]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200405021]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[A general hierarchical framework of news video process is presented. It divides the news video process into three levels: syntax segmentation level, semantic labeling level and abstraction level. Some key techniques related to these levels are described and solutions of them are introduced. The proposed framework overcomes the shortcomings of traditional news video process methods, which are limited to the content-based segmentation and process based  on the single media feature. It acquires the semantic content by the analysis of audio-visual features synthetically. Experiments are carried out on a news video process prototype called NVPS, which validates the feasibility of the framework. Three methods, namely story detection, caption detection and anchor detection methods are tested on NVPS. The results reach to the detection precision of 88%, 86% and 86% respectively, which prove the efficiency of the layered framework in the semantic content analysis of news videos.]]></description>
<pubDate>2013/5/3 9:19:53</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[XIE Yuxiang,LUAN Xidao,WU Lingda,LAO Songyang and WANG Weiwei]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>XIE Yuxiang,LUAN Xidao,WU Lingda,LAO Songyang and WANG Weiwei</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200405021]]></guid><cfi:id>761</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Design and Implementation of a Controlling and Measuring Systemfor the Testing of Rocket Engines Based on Network Technology]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200404006]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The design and implementation of a maltitask controlling and measuring system for the testing of rocket engines are presented. The  system is developed under Windows2000,based on the network technology. The architectures of hardware and software of the system are described in detail .The system is implemented and its function is verified by the testings of engines.]]></description>
<pubDate>2013/4/27 3:07:23</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[CHEN Hui,JIANG Chunling and XIE Lunya]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>CHEN Hui,JIANG Chunling and XIE Lunya</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200404006]]></guid><cfi:id>760</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[The Multi-level and Multiobjective Optimization DesignMethod for Two Dimensional Scramjet Inlet]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200403001]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[A multi-level and multiobjective optimization (MLMOO) design method for two-dimensional scramjet inlet was established. Total pressure recovery coefficient, static pressure rise and drag coefficient were selected as performance objective functions to form the multiobjective optimization problem (MOP) of the two-dimensional scramjet mixed compression inlet with 4 external compression ramps and 2 internal compression ramps. The concept of multi-level design was introduced into the inlet performance analysis, one dimensional analysis method and computational fluid dynamics (CFD) method were used on the different stages during the optimization design process. To avoid converging to local optimal solutions and using gradient information which was hard to reach for numerical simulation, a multiobjective hybrid genetic algorithm was employed to find Pareto-optimal solutions in one single run for the present MOP. Following the MLMOO design method, the higher performance scramjet inlet would be worked out steadily.]]></description>
<pubDate>2013/4/27 3:07:05</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LUO Shibin,LUO Wencai,DING Meng and WANG Zhenguo]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LUO Shibin,LUO Wencai,DING Meng and WANG Zhenguo</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200403001]]></guid><cfi:id>759</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Influence of the Ignition Transient on the Mechanical Response ofComposite Solid Propellants]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200403002]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Based on an effective nonlinear viscoelastic model, the differential constitutive equation and strain-rate equation of solid composite propellants are induced.Pressure/strain and pressurization rate/strain rate are linear correlation during the ignition transient.And the coefficient is the initial modulus of composite solid propellants.]]></description>
<pubDate>2013/4/27 3:07:06</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[ZHONG Tao,ZHANG Weihua and WANG Zhongwei]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>ZHONG Tao,ZHANG Weihua and WANG Zhongwei</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200403002]]></guid><cfi:id>758</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Attitude Control System Design of the Maneuverable ReentryVehicle for Variable Target]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200403003]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Based on the attitude feedback structure and in improvement of the system stability improving, the system feedback parameters are confirmed for adapting the flight parameters. By the simulation and analysis of six degrees of freedom, it is proved that the system can satisfiy the need of the variable target and the control effectiveness is good.]]></description>
<pubDate>2013/4/27 3:07:06</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[GUO Zhenyun and ZHU Bopeng]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>GUO Zhenyun and ZHU Bopeng</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200403003]]></guid><cfi:id>757</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Photogrammetry Based on the Image SequenceAcquired by the Satellite Formation]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200403004]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In modern satellite photogrammetry, clusters of low-performancesatellite flying in formation may provide enhanced performance over singlehigh-performance satellite. This is especially true for photogrammetry based on the satellite formation where stereographic imaging may provide higherresolution data. A block is formed by the image sequence acquired with the satellite formation, and the block aerotriangulation by bundlemethod is applied to get coordinateof ground point. Some satellite formation suit for satellitephotogrammetry is introduced and  the factors which effect accuracy ofsatellitephotogrammetry is described. The experimental result is given, which would be useful for the development of satellite photogrammetry based the satellite formation.]]></description>
<pubDate>2013/4/27 3:07:06</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LU Hongwei<sup>1</sup>,QIU Zhiqiang<sup>1</sup>,YU Qifeng<sup>1</sup> and WANG Wei<sup>2</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LU Hongwei<sup>1</sup>,QIU Zhiqiang<sup>1</sup>,YU Qifeng<sup>1</sup> and WANG Wei<sup>2</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200403004]]></guid><cfi:id>756</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Simulink Modeling & Simulation Analysis of the Attitude ControlSystem on Three-channel of the Launch Vehicle]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200403005]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Exampled by a certain launch vehicle, the modeling method and modelingprocess with Simulink to mathematicalsimulation on three-channel for the vehicle attitude control system are described.The problem of the local surge of the calculated data due to the so-called freeze time method during the simulation process is analyzed and the resolvent is given. Algebraic loop problem encounteredinSimulinkmodeling of this large scale system is discussed and the resolvent is given.]]></description>
<pubDate>2013/4/27 3:07:06</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[SUN Zhibing and DAI Jinhai]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>SUN Zhibing and DAI Jinhai</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200403005]]></guid><cfi:id>755</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[The Control of the Satellites Coplanar Formation Flying]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200403006]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The figure of the relative kinematical track of the formation flying will change which is in an ellipse because of the disturbing force from which the satellitessuffer. A simple way of control is developed that saves the fuel, that is, in Hill orbital coordinates, through themeasurement of x-axis and z-axis, the control of the small jet engine will eliminate the phase excursion of the center of the ellipse and the non-coplanarity of the orbit of satellites.]]></description>
<pubDate>2013/4/27 3:07:06</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[WEN Yuanlan<sup>1</sup>,SONG Yisheng<sup>2</sup> and WEN Jing<sup>3</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>WEN Yuanlan<sup>1</sup>,SONG Yisheng<sup>2</sup> and WEN Jing<sup>3</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200403006]]></guid><cfi:id>754</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Concurrent Subspace Design Method Based on the EvolutionarySearch Strategy]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200403016]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The concurrent subspace design is an effective method in multidisciplinary design optimization, but its search strategy has two shortcomings: one with limited ability of finding global optimum solution, and calculation complexity. To remedy the shortcomings of this search strategy, genetic algorithm is adopted and an improved current subspace design method is presented. The design process is introduced. The optimizing calculations for a test problem are finished and the results are satisfactory.]]></description>
<pubDate>2013/4/27 3:07:06</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[SUN Pizhong,XIA Zhixun and ZHAO Jianmin]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>SUN Pizhong,XIA Zhixun and ZHAO Jianmin</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200403016]]></guid><cfi:id>753</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[MDO Research Involving Control Disciplinary in the Design Loop]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200402001]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[This paper presents a robust controller design approach based on the design parameters uncertainty, which combines this method with multidisciplinary design optimization, and realizes MDO in the design loop in  control disciplinary. The parallel optimization design of aerodynamics and control disciplinary for a given tailess MAV is studied to illustrate that this method is feasible.]]></description>
<pubDate>2013/4/22 10:35:42</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[ZENG Qinghua and ZHANG WeiHua]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>ZENG Qinghua and ZHANG WeiHua</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200402001]]></guid><cfi:id>752</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Hybrid Genetic Algorithm and Its Application to the Optimal AscentTrajectory Design of the Vehicle]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200402002]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The optimal ascent trajectory design of the vehicle is an optimal control problem with strict terminal constraints and variable final time. The classical algorithms always encounter the problems of high sensitivity to initial guess and local convergence in solving this problem. Aiming at these problems, genetic algorithm (GA) which is of good global convergence is applied to designing the optimal ascent trajectory .In order to improve the convergence rate of GA and overcome its premature problems, two hybrid GA (HGA) combining the merits of GA with those of simplex method are proposed. The computational results testify that the two HGA are effective global optimization approach for solving complex problems, and they can successfully solve the optimal control problems with variable final time.]]></description>
<pubDate>2013/4/22 10:35:42</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LUO Yazhong,TANG Guojin and ZHOU Lini]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LUO Yazhong,TANG Guojin and ZHOU Lini</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200402002]]></guid><cfi:id>751</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Stability Simulation of the Spinning Ballistic Missile]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200402003]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[To survive the laser's attack, ballistic missiles can spin to reduce the dwell time of the beam at a particular point on the missile. The realzation of stability is different from before. We design the missile's autopilot by the method of classical control theory and MFD technology. The simulation result shows that the unsteady aerodynamic ballistic missile can fly stablly at the low spinning rate during the first boosting phase.]]></description>
<pubDate>2013/4/22 10:35:42</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[YUAN Tianbao<sup>1</sup>,LIU Xinjian<sup>1</sup>,SHEN Huijun<sup>1</sup>,QIN Zizeng<sup>1</sup>,GU Lixiang<sup>2</sup> and FU Weixian<sup>2</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>YUAN Tianbao<sup>1</sup>,LIU Xinjian<sup>1</sup>,SHEN Huijun<sup>1</sup>,QIN Zizeng<sup>1</sup>,GU Lixiang<sup>2</sup> and FU Weixian<sup>2</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200402003]]></guid><cfi:id>750</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Simulation of Parachute Final Inflation Phase]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200402004]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[A final inflation model for parachutes was established. The forebody, suspension lines and canopy were modeled as a series of elastically connected mass nodes. The flow field inside the canopy was two-dimensional inviscid, incompressible flow. The model was used to calculate the variations of the canopy shape, the variations of canopy projection area and the tension of the suspension line during the final inflation phase. Numerical results were compared with the experimental data and found to be in agreement.]]></description>
<pubDate>2013/4/22 10:35:42</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[PENG Yong,ZHANG Qingbin and QIN Zizeng]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>PENG Yong,ZHANG Qingbin and QIN Zizeng</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200402004]]></guid><cfi:id>749</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Experimental Study of Supersonic Combustion of Kerosene]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200401001]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Research on the ignition and combustion performance of kerosene in a direct-connected scramjet model was conducted. Successful ignition and sustain combustion were achieved in the supersonic combustor. The distribution of wall pressure was measured to validate the combustion performances under different conditions. The test results indicate that kerosene fuel can be self-ignited when the equivalent fuel-air ratio varies from 0.27 to 1.46. The strut and cavity structure are important for the ignition and stable supersonic combustion of kerosene in the model scramjet. When a little hydrogen was injected with kerosene, the ignition and combustion performance was greatly improved. Too thick strut, too high equivalent fuel/air ratio, too much kerosene injected into the first combustor can make the combustor choke, consequently, affect the work of the isolator and air-heater nozzle.]]></description>
<pubDate>2013/4/22 10:35:29</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[YU Yong,DING Meng,LIU Weidong,LIANG Jianhan,SHEN Chibing,ZHOU Jin and WANG Zhenguo]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>YU Yong,DING Meng,LIU Weidong,LIANG Jianhan,SHEN Chibing,ZHOU Jin and WANG Zhenguo</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200401001]]></guid><cfi:id>748</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Research on Aerodynamic Characteristics of Re-entryFigure in Transition Domain]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200401002]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The transitional flow over a complicated sphere-bicone figure was simulated by DSMC method. The isotherm and pressure contour were shown in the near-continuum region and the drag coefficient and the pressure coefficient distribution curves of the surface were also presented at different Knudsen numbers and different Mach numbers. Comparison analysis of the drag coefficient was carried out between simulated results and approximation data estimated by the bridging-function formula.]]></description>
<pubDate>2013/4/22 10:35:29</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[CHEN Weifang,WANG Quanli and WU Xiong]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>CHEN Weifang,WANG Quanli and WU Xiong</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200401002]]></guid><cfi:id>747</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Independent Component Analysis for Fault Detection ofthe Liquid Propellant Rocket Engine]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200401004]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The experimental data analysis, feature extraction, fault detection and diagnosis are focuses in recent rocket engine study. However, in practice, because of noises and the mixing of signals due to different components, the signal-to-noise ratio (SNR) is always low, so the signal analysis and the feature extraction are quite difficult. This results in the difficulty of fault detection and diagnosis. By applying independent component analysis (ICA) to the separation of source signals from mixed signals, high quality signals have been extracted for further studies. The example reveals this method is very effective.]]></description>
<pubDate>2013/4/22 10:35:29</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[REN Haifeng,HU Xiaoping,WEI Pengfei and WU Jianjun]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>REN Haifeng,HU Xiaoping,WEI Pengfei and WU Jianjun</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200401004]]></guid><cfi:id>746</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Analysis and Prediction of the Fluctuating Pressure Induced byRotated Aircraft at Transonic Mach Numbers]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200401005]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Fluctuating pressure provides an important basis for the analysis of structure response and for the study of the dynamics environment. A new technical approach is presented, by which numerical simulation of the  mean fluid field is integrated with the engineering prediction model based on experiments. For the transonic rotated aircraft, the surface fluctuating pressure environment is analyzed and predicted. And the fluctuating pressure coefficient curves and the power spectral density curves are presented at different transonic Mach numbers and different angles. The results essentially accord with the experiment results.]]></description>
<pubDate>2013/4/22 10:35:29</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LONG Wanhua<sup>1</sup>,CHEN Weifang<sup>2</sup> and SONG Songhe<sup>1</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LONG Wanhua<sup>1</sup>,CHEN Weifang<sup>2</sup> and SONG Songhe<sup>1</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200401005]]></guid><cfi:id>745</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[SPH Simulation of Rayleigh-Taylor Instability]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200401006]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Rayleigh-Taylor instability of fluid interface was simulated by the smoothed particle Hydrodynamics(SPH) method. The growth of the interface instability was presented, and the fungus appearance of the instability was obtained. The characters showed by the numerical results indicate that the numerical results are logical, and the SPH method has the potential to simulate Rayleigh-Taylor instability.]]></description>
<pubDate>2013/4/22 10:35:29</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[TANG Wenhui<sup>1</sup> and MAO Yiming<sup>2</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>TANG Wenhui<sup>1</sup> and MAO Yiming<sup>2</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200401006]]></guid><cfi:id>744</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[A Research of the Technique of Optimizing the Orbit-alteration for the Exact-landing of Aerocraft by Using Evolution-algorithm]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200506001]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[This paper deals with the exact-landing of aerocraft and discusses a kind of the technique of optimizing the orbit-alteration for the exact-landing of aerocraft by using evolution-algorithm, based on single-pulse on orbital apogee and common single-pulse.]]></description>
<pubDate>2013/4/10 0:00:00</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[ZHAO Jiankang and DAI Jinhai]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>ZHAO Jiankang and DAI Jinhai</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200506001]]></guid><cfi:id>743</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[The Aerodynamic and Structural Design of SupersonicQuiet Wind Tunnel]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200506002]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[A basic idea of a quiet wind tunnel is described. A supersonic quiet wind tunnel(SQWT-120) is designed and built. SQWT-120 designed Mach number is 4.0, the nozzle outlet diameter is 120mm, Re is 0.46～1.78×10<sup>7</sup>and the operation duration is 6-60 seconds. The conclusions of calibrations demonstrate the actual flow Mach number is 3.8, ΔM/M is ≯±1.2% between x=160mm and x=438mm. The unsteady pressure disturbances are not larger than 0.1% before x=450mm, the operation time is 15s. The results show that the wind tunnel can be used to study the steady flow and unsteady flow.]]></description>
<pubDate>2013/4/10 0:00:00</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[ZHOU Yongwei]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>ZHOU Yongwei</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200506002]]></guid><cfi:id>742</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[The Damage-mitigating and Life-extending Control for Liquid-propellant Rocket Engine Based on Multiobjective Optimization]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200506003]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The damage-mitigating and life-extending control (DMLEC) based on multiobjective optimization (MOO) is presented by DMLEC policy analysis and synthesis. The progress of solving DMLEC policy by using nonlinear programming is analysed which combines with the dynamics modelling, the structural analysis of turbine blade and the damage modelling of a certain liquid-propellant rocket engine.Then, the start-up process of the LRE under the control of DMLEC is simulated. The result indicates that the damage of blade is mitigated and the service life of LRE is extended considerably while the system performance is only debased a little.]]></description>
<pubDate>2013/4/10 9:23:44</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[WEI Pengfei,WU Jianjun,LIU Honggang and CHEN Qizhi]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>WEI Pengfei,WU Jianjun,LIU Honggang and CHEN Qizhi</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200506003]]></guid><cfi:id>741</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[The Large Eddy Simulation of Two-DimensionalSupersonic Mixing Layer]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200505018]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Large eddy simulations are conducted to investigate the coherent structures of a two-dimensional supersonic mixing layer.The Governing equations of large scale eddies are solved with fifth-order WENO scheme and the effect of small scale eddies is simulated with Smagorinsky subgrid scale model.The results show that the development procedure of large structures and reveal the behavior of large eddies.Frequency spectrum analysis of the unsteady pressure data is performed to investigate the acoustic characteristics of different streamwise location in the mixing layer.Time-averaged velocity profiles obtained from the simulation are consistent with the experimental data.]]></description>
<pubDate>2013/4/8 11:10:35</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[SUN Mingbo,LIANG Jianhan,JIN Liang,HOU Zhongxi and WANG Zhenguo]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>SUN Mingbo,LIANG Jianhan,JIN Liang,HOU Zhongxi and WANG Zhenguo</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200505018]]></guid><cfi:id>740</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[The IR Radiation Characteristic of Exhaust Plumeof the Liquid Rocket Engine]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200505019]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The IR radiation characteristic of exhaust plume of the liquid rocket is numerically calculated. Based on the established HITRAN database and the numerical simulation results of the exhaust plume field, the radiation transmission equation is numerically solved. The absorption and radiation of the atmosphere are considered. The calculation results indicate that the transmission conditions, height and angle, exert important influence on the distribution of spectrum intensity. The spectral irradiances achieved by solving the RTE are compared with the test data, which show that the calculation method is feasible and the solution is proper.]]></description>
<pubDate>2013/4/8 0:00:00</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[NIE Wansheng,YANG Junhui,HE Haobo,FENG Songjiang and ZHUANG Fengchen]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>NIE Wansheng,YANG Junhui,HE Haobo,FENG Songjiang and ZHUANG Fengchen</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200505019]]></guid><cfi:id>739</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[A Novel Satellite Autonomy Architecturewith Self-organization for Multi-satellite Coordination]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200505020]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[A novel satellite autonomy architecture with self-organization (SAASO) for multi-satellite coordination is put forward to fulfill the autonomous control demands of multi-satellite systems. The demands and characteristics of the autonomous control are analyzed. The components, functions and relationships of agents are introduced. The mechanism of the autonomous control based on SAASO is expounded, and the form of self-organization is discussed. SAASO is designed for various space missions and various autonomous satellites, thus it has generality to a certain extent.]]></description>
<pubDate>2013/4/8 0:00:00</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[ZHANG Jian and DAI Jinhai]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>ZHANG Jian and DAI Jinhai</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200505020]]></guid><cfi:id>738</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[The Dynamic Model of a Parachute Systemwith the Inverted ‘Y’ Suspension]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200505022]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The dynamic model of the parachute system with the inverted ‘Y’ suspension is established, which is widely used in recovery systems. The model is comprised of the general rigid-body equations considering apparent mass and the modeling method of suspension system based on the assumption of “equilibrium points”. A simulation analysis for a spaceship's airdrop experiment is carried out and the validity of models is showed by the experiment data.]]></description>
<pubDate>2013/4/8 11:10:35</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[SONG Xumin,QIN Zizeng,CHENG Wenke and GUO Shuwei]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>SONG Xumin,QIN Zizeng,CHENG Wenke and GUO Shuwei</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200505022]]></guid><cfi:id>737</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[The Sound Velocity of the Solids under High Pressure]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200504001]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The sound velocity of the materials at sufficiently high pressure is an important quantity reflecting material qualities under extreme conditions. In this paper, from the shock adiabatics and the Gruneisen equation of state, an isentropic, which corresponds to shock adiabatics, is delivered, and the formulas of calculating sound velocity along isentropic and isothermal compression, as well as the Hugoniot curves, are presented. The Hugoniot sound velocities of aluminum and tungsten are calculated. The calculated results are in good accord with the experimental results.]]></description>
<pubDate>2013/4/8 11:10:21</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[TANG Wenhui]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>TANG Wenhui</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200504001]]></guid><cfi:id>736</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[A Preliminary Research on the Performance of HydroreactiveAluminium Metal Fuel]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200504002]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The model of bi-reaction region of hydroreactive metal fuel is presented. In consideration of chemical reaction process, the thermodynamics character of hydroreactive mental fuel is analyzed. The influence of prescription and other factors on motor performance are investigated preliminarily.]]></description>
<pubDate>2013/4/8 11:10:21</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LI Fang,ZHANG Weihua,ZHANG Wei,YANG Shiqing and XIA Zhixun]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LI Fang,ZHANG Weihua,ZHANG Wei,YANG Shiqing and XIA Zhixun</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200504002]]></guid><cfi:id>735</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[The Object-oriented Flexible Control Model for Ground Test of GasGenerators and Its Realization]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200504003]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In order to meet the requirements of the ground test control of gas generators, We analyze the control behavior, and puts forward an advanced object-oriented flexible control model (OOFCM) for ground test of gas generators, which accords with the developing direction of the measurement and test technology. Based on the OOFCM, a flexible control system (FCS) is realized, which can meet the requirements of the ground test control of all kinds of gas generators. The FCS has been used in the test successfully. Compared with the older test control system, the new system has higher dependability, simpler structure and more flexible manipulation.]]></description>
<pubDate>2013/4/8 11:10:21</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LI Haitao and WANG Zhenguo]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LI Haitao and WANG Zhenguo</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200504003]]></guid><cfi:id>734</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[A Research on the Numerial Value of the Nonlinear Flow of theOscillating Rectangular Wing]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200504004]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[A numerical method is developed to simulate the unsteady flows involving moving boundaries. For this method, dynamic unstructured grid technique was used, and a MUSCL type finite volume scheme was constructed to discretize the 3D unsteady Euler equations described in ALE frame. The deformation of unstructured grid was implemented by spring analogy. The whole methodology was then applied to simulate the unsteady transonic flow of the three-dimensional rigid wing undergoing a forced sinusoidal motion in angle of attack. Computational results are in agreement with the experimental data, and the nonlinear flow characteristics caused by the fluid and structure interaction was clearly obtained. It can be concluded from the research that the whole methodology presented here is adequately accurate and reliable, and can be applied in aeroelasticity study and a series of fluid and structure interaction problems.]]></description>
<pubDate>2013/4/8 11:10:21</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[GUO Zheng<sup>1</sup>,TAN Jie<sup>2</sup> and LIU Jun<sup>1</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>GUO Zheng<sup>1</sup>,TAN Jie<sup>2</sup> and LIU Jun<sup>1</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200504004]]></guid><cfi:id>733</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[The Condensation Method with Similar Shape Element for theSolution of Viscoelastic Interface Crack]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200504007]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The condensation method for the analysis of viscoelastic interface crack with similar shape element is put forward. By this method, similar shape elements are generated near the crack tip, forming a substructure with a large number of similar shape elements. And then the large number of freedom degrees in substructure is condensed out. Identity of stiffness matrix between the similar shape elements is used fully during the process of condensation, The tension of bi-viscoelastic and elastic-viscoelastic material rectangle plate with the single edge crack is solved to illustrate the use of this method.]]></description>
<pubDate>2013/4/8 11:10:21</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LIU Fu,REN Junguo and ZHOU Jianping]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LIU Fu,REN Junguo and ZHOU Jianping</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200504007]]></guid><cfi:id>732</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[The Analysis of Data Mining Strategy in Fault Detection andDiagnosis of the Liquid Rocket Engine]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200503001]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[By analyzing the working characteristics of the liquid rocket engine, strategies of applying data mining from the point of view of the data warehouse for FDD of LRE are proposed. The data mining methods possibly applicable to different topics in the fault detection and diagnosis of LRE are compared. Primary research results show that such data mining methods as clustering, classification, association, time-series analysis and outlier analysis are feasible in the FDD of LRE.]]></description>
<pubDate>2013/4/8 11:09:48</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[HU Xiaoping<sup>1</sup>,ZHANG Lijuan<sup>2</sup>,WANG Yanmei<sup>2</sup> and LI Zhoujun<sup>2</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>HU Xiaoping<sup>1</sup>,ZHANG Lijuan<sup>2</sup>,WANG Yanmei<sup>2</sup> and LI Zhoujun<sup>2</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200503001]]></guid><cfi:id>731</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Partical Simulation of Low-speed Flow in a Round Tube]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200503002]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The information preservation method (IP) is applied to calculate the low-speed flow in a tube. The results are compared with that of the experiment and the datum tallies well. The results of IP method is better than NS equations'. The study indicates that IP method is an effective method to simulate the low-speed flow in a tube. Furthermore, better results and higher computer efficiency can be achieved.]]></description>
<pubDate>2013/4/8 0:00:00</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[CHEN Weifang,LI Zhuang and YIN Le]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>CHEN Weifang,LI Zhuang and YIN Le</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200503002]]></guid><cfi:id>730</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Numerical Simulation of the Temperature Field in the ThinShell Irradiated by Mobile Laser Beam]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200503003]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The temperature distribution of the cylindrical shell irradiated by mobile laser beam is studied. Based on the method of Fourier series expansions, an analytical solution of the temperature field is deduced for the thin cylindrical shell, irradiated by intensive laser beam in four different motion modes，and programs are coded for computation. Numerical simulation results of this method are identical with those of finite element method. Finally, we analyze the effect of the rotating angular velocity and moving velocity on its temperature field under laser irradiation. The conclusion is drawn that temperature rise is  most prominent in the case of periodic irradiation. Numerical results provide evidence for the laser resistant radiation of missiles in theory.]]></description>
<pubDate>2013/4/8 11:09:48</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[WU Fei,ZHOU Jianping and LEI Yongjun]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>WU Fei,ZHOU Jianping and LEI Yongjun</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200503003]]></guid><cfi:id>729</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[The Unsteady Flow Field Calculation witha Dual-time Stepping Method]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200503006]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Based on a 3rd order weighted NND scheme, a dual-time stepping method is used to solve the 2D unsteady Euler equations and the flow field of a forced vibration airfoil at transonic speed is simulated numerically. The influence of the inner iteration steps, the inner iteration tolerance and the magnitude of physical time step on the calculation results and efficiency are discussed. The results achieved with the present methodal are compared with the experimental results.]]></description>
<pubDate>2013/4/8 11:09:48</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[ZHAO Haiyang,LIU Wei and REN Bing]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>ZHAO Haiyang,LIU Wei and REN Bing</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200503006]]></guid><cfi:id>728</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[The Analytical Method for the Bending Problem ofOrthotropic Rectangular Plate Structure]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200503021]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[A plate structure is a structure made up of several plates. To solve the bending problem of orthotropic plate, a general analytical solution of partial differential equation for transverse displacement function of orthotropic rectangular plates in bending must be worked out. It can be used to solve the bending problem for arbitrary boundaries and arbitrary load. For each plate; some edges are independent which can be calculated by boundary conditions, while some edges are connected by other plates which can be calculated by continuous conditions. With the equations made up of these conditions, it can be used to solve all the integral constants in general solutions. For example, a water tank under hydrostatic pressure with the edges simply supported at the top and fixed at the bottom has been calculated.]]></description>
<pubDate>2013/4/8 11:09:49</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[YUAN Duancai,TANG Guojin and HUANG Yan]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>YUAN Duancai,TANG Guojin and HUANG Yan</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200503021]]></guid><cfi:id>727</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Relative Motion Analysis of the Spacecraft Formation Flight inHighly Elliptic Orbits]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200502001]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The spacecraft on highly elliptic orbits fly over their apogee in the most part of their cycles, so this kind of orbit is usually applied in the satellite communication, the observation of celestial bodies and the exploration of space magnetic fields. The kinematics of multi-spacecraft formation is required to deal with the above space missions. Formulations of the relative motion on highly elliptic orbits are presented by kinematic method. On the basis of them, the necessary condition is given to maintain the long-term and close formations. The influence of relative orbital elements on the precision of this linear simplified formulation is discussed and on the dynamic characteristics of relative trajectories. The simulation results show that the formulations are more precise at the orbit apogee. If the relative orbital elements were selected properly, the design formation orbit would satisfy the requirements of the aforementioned missions.]]></description>
<pubDate>2013/3/25 4:57:30</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[AN Xueying,YANG Leping,ZHANG Weihua and XI Xiaoning]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>AN Xueying,YANG Leping,ZHANG Weihua and XI Xiaoning</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200502001]]></guid><cfi:id>726</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[CSP Model of the Relay Satellite Scheduling]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200502002]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The relay satellite, circulating on the GEO (Geographic Earth Orbit), can view the user spacecraft on the LEO (Low Earth Orbit) and the MEO (Middle Earth Orbit) directly as well, and view the ground station directly. The relay satellite can be seen as the bridge between the user spacecrafts and the ground station. The scheduling problem within TDRSS (Tracking and Data Relay Satellite System) is a very important problem. It analyses the characteristics and the constraints of the relay satellite scheduling, and then builds the CSP (Constraints Satisfaction Problem) model of the problem based on CSP theory. The CSP model is solved with STK (Satellite Tool Kits) and simulation method. Computational experiments indicate that the performance of the CSP model is quite good.]]></description>
<pubDate>2013/3/25 4:57:31</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[FANG Yanshen,CHEN Yingwu and GU Zhongshun]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>FANG Yanshen,CHEN Yingwu and GU Zhongshun</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200502002]]></guid><cfi:id>725</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Finite Element Analysis of the Turbine Blade StructuralCharacteristics for Liquid Propellant Rocket Engine]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200502007]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[It is necessary to analyze the structural characteristics of the engine key components so as to be able to predict the engine life and  mitigate the components damage, and extend the engine life for improving the reliability, availability and maintainability of liquid rocket engines. The model of the turbine rotor blade with finite element analysis for the newly developing large-thrust liquid rocket engine is set up. Based on these models, characteristics analysis of structural dynamics such as modal analysis under undamped free vibration, harmonic response under undamped forced vibration and transient response under damped forced vibration, is performed respectively. Meanwhile, natural frequencies and mode shapes, harmonic response and transient response of a single turbine rotor blade, are also obtained.]]></description>
<pubDate>2013/3/25 4:57:38</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[WEI Pengfei,WU Jianjun and CHEN Qizhi]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>WEI Pengfei,WU Jianjun and CHEN Qizhi</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200502007]]></guid><cfi:id>724</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Evaluation of the Missile Precision by Using theConstruction Simulation]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200502026]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The prior distribution parameters of the falling points are obtained by using the construction simulation, then the credibility of the prior information is acquired by consistent test. The bayesian estimations of the mean and variance of the falling points are obtained by considering the credibility of the prior information. An example validates that it is successful to use the simulation information, and Bayesian estimation on considering the credibility has a better confidence level.]]></description>
<pubDate>2013/3/25 4:57:59</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[YANG Huabo<sup>1</sup>,ZHANG Shifeng<sup>1</sup>,CAI Hong<sup>1</sup> and YUE Yaoming<sup>2</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>YANG Huabo<sup>1</sup>,ZHANG Shifeng<sup>1</sup>,CAI Hong<sup>1</sup> and YUE Yaoming<sup>2</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200502026]]></guid><cfi:id>723</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Research of GAs for the Problems Restricted by the ImplicitFormula in the Integral Design Optimization]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200502027]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Genetic algorithm is altered to solve the problems  restricted by the implicit formula on the basis of the research on schema theorem and canonical genetic algorithm theorem.The simulation results show that its performance of searching the global optimal solution and rapid convergence is better than that of some other GAs. It is a good way in numerical computing.]]></description>
<pubDate>2013/3/25 4:58:00</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[ZHAO Jianmin,XIA Zhixun,Hu Jianxin and LUO Zhenbing]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>ZHAO Jianmin,XIA Zhixun,Hu Jianxin and LUO Zhenbing</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200502027]]></guid><cfi:id>722</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[The Principle of Direction Detemination with a SingleGeostationary Safellite and the Experiment in GPS]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200501006]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[A new method of direction determination with a single geostationary satellite is presented. Also an experiment is done in order to validate the method with GPS satellites. The result shows that the precision of direction determination can be higher than 0.05°when the baseline length is about 3 meters long; so it proves that the principle of direction determination with a single geostationary satellite is right and feasible.]]></description>
<pubDate>2013/3/25 4:48:24</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[ZHENG Chong<sup>1</sup>,LI Yanxing<sup>2</sup> and WU Jie<sup>1</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>ZHENG Chong<sup>1</sup>,LI Yanxing<sup>2</sup> and WU Jie<sup>1</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200501006]]></guid><cfi:id>721</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[On Three-axis Mount Tracking Algorithms]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200501027]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In order to study a three-axis overhead tracking problems, α-degenerative tracking algorithm is discussed. A completely degenerate tracking and a three-step tracking algorithm are proposed. It is proved theoretically that they can solve overhead tracking problems. Furthermore, by applying the first algorithm, it is simulated that the three-axis tracks to a satellite orbits abou 2000km form the Earth. The simulating data shows that the completely degenerate algorithm keeps the rotation speed of each axis within 0.56 degrees per second. The second tracking algorithm is used in the three-axis automatic tracking experiment. It shows that the three-step tracking can solve the overhead tracking problem.]]></description>
<pubDate>2013/3/25 4:48:46</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[NI Guyan,HUA Weihong,JIANG Zongfu and ZHAO Yijun]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>NI Guyan,HUA Weihong,JIANG Zongfu and ZHAO Yijun</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200501027]]></guid><cfi:id>720</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Viscoelastic Spectral Stochastic Finite Element]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200606001]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[A kind of viscoelastic spectral stochastic finite element method (VSSFEM) was developed and stochastic analysis of solid rocket motor grains was presented. Considering the randomness of solid propellant Poisson's ratio, viscoelastic spectral stochastic finite element formulations were derived from the incompressible or nearly incompressible viscoelastic incremental finite element method and orthogonal expansion theory. Finally, stochastic analysis of a hollow cylindrical grain with elastic restraint was presented. Analysis of examples indicates that this method is efficient and effective for stochastic analysis of viscoelastic body.]]></description>
<pubDate>2013/3/14 0:00:00</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[TIAN Sipeng,LEI Yongjun and TANG Guojin]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>TIAN Sipeng,LEI Yongjun and TANG Guojin</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200606001]]></guid><cfi:id>719</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Schematic Study of Mid-course Trajectories for the Boost-glide Missiles]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200606002]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The dimensionless equations of motion for mid-course of the boost-glide trajectory are presented and the trajectory optimization problems are solved with nonlinear programming method (NLP). Firstly, the maximum range trajectories with varied initial velocity, inclination of the velocity and maximum lift-to-drag ratio of the vehicle were generated. Then the minimal accumulated heating load and the maximum range trajectories with stagnation heating rate and load factor constraints were investigated. The numerical results of first kind trajectories show the influence of initial condition on the maximum range trajectories. The second kind of the optimal glide trajectory was compared with the pure ballistic trajectory under the same condition. The results show that the maximum heating rate of glide reentry declines while the heat load of the glide trajectory increases. Furthermore, the flight time of the glide is within the tolerance of the Thermo Protection System (TPS) of conical shape maneuver reentry vehicles.]]></description>
<pubDate>2013/3/14 10:39:53</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[YONG Enmi,TANG Guojin and Chen Lei]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>YONG Enmi,TANG Guojin and Chen Lei</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200606002]]></guid><cfi:id>718</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Precise Manufacture of CompositeBearing Cylinder by Bladder-assisted RTM Process]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200606003]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The equation for calculating Bladder dimension is derived based on the relationship between bladder pressure and the inner diameter of composite bearing cylinder. Effects of bladder pressure on the thickness, fiber volume fraction and bending properties of composite bearing cylinder were investigated. The composite bearing cylinder was manufactured by bladder-assisted resin transfer molding(BARTM) process. The experimental result shows that higher bladder pressure decreases thickness of composite bearing cylinder, increases fiber volume fraction and improves the bending properties. This indicates that composite bearing cylinder can be manufactured with precise inner diameter by BARTM process with a proper bladder pressure.]]></description>
<pubDate>2013/3/14 10:39:53</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[DU Gang,ZHANG Minglong,ZENG Jingcheng,LIU Jun,PENG Chaoyi and XIAO Jiayu]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>DU Gang,ZHANG Minglong,ZENG Jingcheng,LIU Jun,PENG Chaoyi and XIAO Jiayu</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200606003]]></guid><cfi:id>717</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Solving the Optimal Multi-impulse Rendezvous ProblemBased on the Dynamic Programming]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200606008]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The multi-impulse rendezvous problem is a key research field of astronautics. Firstly, based on the operational research, this problem was converted to a multi-phase-multi- dimension dynamic programming question. Then the multi-phase-two-dimension dynamic programming problem was emphatically analyzed, and the state transfer equations and recursion equations of the performance function were deduced. The solution to the two-impulse and three-impulse problem and the validating examples were given later. ln the end, the dynamic programming idea which uses the evolution algorithm to reduce the dimension of the multi-dimension question was introduced.]]></description>
<pubDate>2013/3/14 10:39:53</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LIU Luhua,TANG Guojian and YU Menglun]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LIU Luhua,TANG Guojian and YU Menglun</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200606008]]></guid><cfi:id>716</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Ritz Method for the Frequencies of Nonlocal Elastic Bar]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200605001]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Ritz method was adopted to study the natural frequency of nonlocal elastic bar. Nonlocal elastic theory, different from classic elastic theory, was presented that the stress of a point is related to the strain of the area around the point, and such a relationship is illustrated by kernel function. Based on Eingen's nonlocal elastic model, a dynamics analysis of nonlocal elastic bar was created by Ritz method with three different kernel functions and the natural frequencies of the bar with two different boundary conditions were supplied. Compared with other methods, this one can deal with different kernel functions. Moreover, its numerical precision is controllable and programming is very convenient.]]></description>
<pubDate>2013/3/14 0:00:00</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LEI Yongjun,ZHAO Xuechuan and TANG Guojin]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LEI Yongjun,ZHAO Xuechuan and TANG Guojin</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200605001]]></guid><cfi:id>715</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Study on the Strategy for Space V-bar RendezvousBased on Combined Maneuver]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200605002]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Based on the combination of a tangential impulse maneuver and a constant continuous radial thrust maneuver, a new strategy for space V-bar rendezvous was presented. The absolute and relative motions of the chaser in combined maneuvers were investigated when it maintains its initial circular orbit. Then the guidance rules of space rendezvous V-bar approach and final translation were derived respectively. For V-bar approach, the chaser makes straight line motion at constant velocity while no constraints need to be considered in the transfer duration and line of sight, resulting in a flexible transfer in time. For V-bar final translation, the chaser's straight line motion is switched from a higher constant speed to a smaller docking velocity at the given position. The process is easy to guide and control, satisfying the requirement of the chaser's transfer to be straight and safe.]]></description>
<pubDate>2013/3/14 10:39:11</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[YANG Leping,ZHU Yanwei and AN Xueying]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>YANG Leping,ZHU Yanwei and AN Xueying</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200605002]]></guid><cfi:id>714</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Application of GPS and ‘GPS-like’ Ranging Technology   inthe States Determination of Double-satellite Formation Constellation]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200605003]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Precise determination of formation states provides the foundation for Formation Constellation to carry out its function. In this paper, the state determination problem of double-satellite formation constellation for earth-observation purpose was discussed. On the basis of GPS, a ‘GPS-like’ ranging technology was introduced to improve the state results. Two mathematical models combining ‘GPS-like’ Ranging technology with GPS were built. In this way, a synchronous initialization method for single differential GPS inter-satellite integer ambiguity and single differential ‘GPS-like’ intra-satellite integer ambiguity were also developed. Finally, these models above were simulated and analyzed. The results indicate that, ‘GPS-like’ observation data, especially the single differential ‘GPS-like’ intra-satellite carrier phase data, significantly improved the states results, and the accuracies of absolute attitudes, relative position and relative clock bias respectively reached rad, m and s. The simulation proves that these methods are correct and model II is more accurate than model I.]]></description>
<pubDate>2013/3/14 10:39:11</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[WANG Wei<sup>1</sup> and HU Limin<sup>1,2</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>WANG Wei<sup>1</sup> and HU Limin<sup>1,2</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200605003]]></guid><cfi:id>713</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[A Soft Release Characteristic Analysis of the Launch VehicleBased on the Finite Element and Rigid-body Mixed Model]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200605004]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The soft release mechanism in a controlled hold-down and release system proposed recently was discussed in this paper and a finite element and rigid-body mixed model was put forward to analyze its release characteristic during launch vehicle liftoff. The rigid-body model was used to describe the movement of the launch vehicle and the finite element method was employed to analyze the finite deformation elastic-plastic contact of the soft release mechanism. The interface compatibility condition was enforced between the launch vehicle and the soft release mechanism. The mixed model was solved with an increment algorithm, which can be used to analyze the influences of the material property of the pin, the shape and size of the soft release mechanism, friction between the die and pin on the entire release time, the launch vehicle velocity and the consumed energy during liftoff.]]></description>
<pubDate>2013/3/14 10:39:11</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[WAN Jun,LI Daokui,TANG Guojin and LEI Yongjun]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>WAN Jun,LI Daokui,TANG Guojin and LEI Yongjun</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200605004]]></guid><cfi:id>712</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Study on Reliability Analysis Method for Liquid RocketEngine in the Case of Zero-failure Data]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200605005]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In the progress of the trial run of liquid rocket engine, the situation of zero-failure data may happen. For zero-failure data, the reliability of the liquid rocket engine was assessed by the least square method with the classical estimation and the Bayes estimation based on the analysis of the life distributing. An analysis of the estimate result was also given. The computational results indicate that the least square method combined with the Bayes estimation is suitable for the reliability analysis of liquid rocket engine in the case of zero-failure data.]]></description>
<pubDate>2013/3/14 10:39:11</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[NING Jiangfan,YAN Xiaoqing and ZHANG Shifeng]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>NING Jiangfan,YAN Xiaoqing and ZHANG Shifeng</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200605005]]></guid><cfi:id>711</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Analysis and Implementation of Satellite Integrated DesignSystem Using MDO]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200604001]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[It is a challenge to integrate Multidisciplinary Design(MD), Multidisciplinary Analysis (MA), Multidisciplinary Optimization (MO) processes with the satellite system design flow. A system-oriented software framework was formulated and implemented for the satellite integrated design by using Variable Complexity Modeling (VCM) method and Production Data Management (PDM) technology. The design conception, structural components and functional characteristics were introduced. Then the software was tested by the example of Lunar Exploration Satellite conceptual design. The results show that it is an effective approach to apply Multidisciplinary Design Optimization (MDO) technology to satellite integrated design.]]></description>
<pubDate>2013/3/25 4:45:51</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[ZHAO Yong,XU Lin,CHEN Xiaoqian and WANG Zhenguo]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>ZHAO Yong,XU Lin,CHEN Xiaoqian and WANG Zhenguo</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200604001]]></guid><cfi:id>710</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Experiment Study of the Mass Flow Control System]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200604002]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Throttling Venturi for cryogenic propellants is the key component of the mass flow control system. The step motor was used to control the displacement of the tapered rod. And water is used in cold test. Through changing operating conditions, throat area and back pressure, the change rule of discharge coefficient and pressure recovery factor were found. Then liquid oxygen was used to modify the results of cold test. The mass flow control system was used in firing test of tripropellant model engine, which shows the system can control the mass flow of liquid oxygen accurately and change the operating conditions successfully.]]></description>
<pubDate>2013/3/25 4:45:52</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[TAO Yujing,TIAN Zhangfu and WANG Zhenguo]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>TAO Yujing,TIAN Zhangfu and WANG Zhenguo</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200604002]]></guid><cfi:id>709</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Experimental Study on Spray Characteristic of Gas-liquidCoaxial Injectors]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200604003]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Spray characteristics of gas-liquid coaxial shear and swirl injectors were studied by conducting experiments. The results suggest that the injector outlet expanding can improve atomization performance; for the two kind of injectors, that is, gas-liquid coaxial swirl injectors and gas-liquid coaxial swirl injectors, with a proper indent length，they have good atomization performance and proper flow performance; and under the same conditions, gas-liquid coaxial swirl injectors have better atomization performance than gas-liquid coaxial swirl injectors.]]></description>
<pubDate>2013/3/25 4:45:53</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[TIAN Zhangfu,WU Jiping,TAO Yujing,ZHOU Jin and WANG Zhenguo]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>TIAN Zhangfu,WU Jiping,TAO Yujing,ZHOU Jin and WANG Zhenguo</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200604003]]></guid><cfi:id>708</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[An Improved Multi-objective Evolutionary Algorithm Based onCrowing Mechanism]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200604005]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Evolutionary algorithms are the main and effective methods in solving multi-objective optimization problems (MOP). Based on the NSGA-Ⅱ algorithm studied and analyzed, we improved its crowding mechanism by introducing the Niche theory to expedite its convergence velocity and improve its convergence precision. The representative test functions show that the improvements have higher computational efficiency and can obtain a reasonable distributing solution; it can also maintain the solutions' diversity.]]></description>
<pubDate>2013/3/25 4:45:55</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[HOU Zhongxi,CHEN Xiaoqing and GUO Liangmin]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>HOU Zhongxi,CHEN Xiaoqing and GUO Liangmin</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200604005]]></guid><cfi:id>707</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Orbit Design for Spacecraft Formation Flying in Eccentric Orbits]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200604006]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Based on the Kepler's equation, a new set of relative motion equations with elliptical reference orbits were derived. The equations are expressed by orbit elements, and can be used directly for formation flying orbit design. Several typical relative motions and the precision of the equations were analyzed. Furthermore, a linear formation and a perpendicular circles formation were suggested. The effectiveness was verified by the simulation results.]]></description>
<pubDate>2013/3/25 4:45:57</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LUO Cheng,GAO Dayuan,SHEN hui and HU Dewen]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LUO Cheng,GAO Dayuan,SHEN hui and HU Dewen</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200604006]]></guid><cfi:id>706</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[General Method for Calculating Spacecraft Collision Probability]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200604007]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[A general method for calculating spacecraft collision probability is developed. In this method the input required to perform a calculation includes the respective state vectors, position error covariance matrices and physical sizes of objects involved. The method is valid for the general case because it only relies on the general form of error covariance matrices. The relative velocity is assumed to be vector having constant direction, and then the collision probability problem can be reduced to two dimensions in encounter plane normal to the relative velocity vector by eliminating the dimension parallel to the relative velocity vector. Three kinds of method resolving the two dimensions problem are developed and compared. Test case results indicate the method is valid and applicable.]]></description>
<pubDate>2013/3/25 4:45:58</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[WANG Hua,LI Haiyang and TANG Guojin]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>WANG Hua,LI Haiyang and TANG Guojin</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200604007]]></guid><cfi:id>705</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[A Modified Contact Algorithm for Smoothed Particle Hydrodynamics]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200604008]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[A contact algorithm which describes the contact interaction between SPH particles by means of Riemann solution was used to calculate the discontinuity of the variables defining the one-dimension fluxes. A weak wave approximation of the Riemann solver was adopted to deal with the weak discontinuity, while the non-iterative Riemann solution was introduced in strong discontinuity. Furthermore Taylor series was used to improve the calculation accuracy on the free boundary. In this case, there was no need to use artificial viscosity for the numerical viscosity of the new SPH algorithm. Compared with the original algorithm, the simulation results show that the modified contact algorithm has a good description of strong discontinuity, and improvement in dealing with the free surface.]]></description>
<pubDate>2013/3/25 4:45:59</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[XU Zhihong,TANG Wenhui and ZHANG Ruoqi]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>XU Zhihong,TANG Wenhui and ZHANG Ruoqi</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200604008]]></guid><cfi:id>704</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Parallel Numerical Simulation and Efficiency Analysis of the FlowField of Supersonic Vehicle]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200603001]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Based on the finite volume method (FVM), OC-TVD scheme and Runge-Kutta method, parallel numerical simulation of the flow field around the hypersonic/supersonic vehicle was performed on a super computer. The parallel computation efficiency was tested with the CPU nodes varied form 2 to 64. The program was tested for its parallel efficiency on the super computer and was applied to the calculation of the flow field around space shuttle. In this way, the large-scale parallel calculating capacity of the program was examined. The results indicate that, given that the load is balanced, the parallel computation on the super computer reaches super-linear speedup. The maximum efficiency ratio reaches 126%, which is far larger than the value on PC cluster parallel platform.]]></description>
<pubDate>2013/3/14 10:38:47</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[FAN Xiaoqiang,LI Hua,LI Xiaoyu and JIA Di]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>FAN Xiaoqiang,LI Hua,LI Xiaoyu and JIA Di</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200603001]]></guid><cfi:id>703</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Preconditioned Methods for Two-dimensional NumericalSimulation at All Speeds]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200603002]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[All speeds control equations were deduced from traditional compressible equations with precondition method and applied to 2D inviscous/viscous flows at all speeds. Jameson central difference scheme, LU-SGS implicit iterative method and round-off control were used to accelerate convergence rates and improve numerical precision. Computations were carried out in the bump flow in a channel, viscous cavity flow and chemical non-equilibrium flow. Numerical results were compared with standard cases. The methods and programs proved to be precise and credible. All these will serve as foundations for further study of integrated flow in combustor and nozzle.]]></description>
<pubDate>2013/3/14 10:38:47</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[PAN Sha,LI Hua,LIAO Shouyi and FAN Xiaoqiang]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>PAN Sha,LI Hua,LIAO Shouyi and FAN Xiaoqiang</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200603002]]></guid><cfi:id>702</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Influence of Injection Mode on Flame Stability in Dual-modeScramjet Combustor]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200603003]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[On the basis of direct-connect scramjet test system simulating flight Mach number 4, different injection modes were compared to study the influence of flame stability on fixed geometry dual-mode scramjet combustor fueled with liquid kerosene and ignited with torch-model ignition. It is indicated that the flame is difficult to stabilize in the flow condition of lower total pressure and total temperature. It is also indicated that the flame stability in dual-mode scramjet combustor is greatly influenced by the injection mode of kerosene.]]></description>
<pubDate>2013/3/14 10:38:48</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LI Dapeng,PAN Yu,LIANG Jianhan,LIU Weidong and WANG Zhenguo]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LI Dapeng,PAN Yu,LIANG Jianhan,LIU Weidong and WANG Zhenguo</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200603003]]></guid><cfi:id>701</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Analysis of Main Parameters of Laser Propulsion Engine andLaunch Trajectory Based on Laser Propulsion]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200603004]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Laser propulsion is an advanced technology with the prospect of wide application. In this paper the main performance parameters of laser propulsion engine was analyzed. Such problems as the optimum specific impulse, the average laser power and the energy consumption of electric current for launching in 2D plane without air drag were addressed. The results show that higher mass ratio can be obtained by utilizing laser propulsion technology while the optimum specific impulse is 12240m/s.]]></description>
<pubDate>2013/3/14 0:00:00</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[HE Zhen,WU Jianjun and YAN Changyu]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>HE Zhen,WU Jianjun and YAN Changyu</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200603004]]></guid><cfi:id>700</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Analysis of the Interfacial Crack in Debonded Layer ofLong Term Storage Solid Motor Grain]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200603005]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The interfacial debonded cracks are liable to occur in the stress relief boot of solid missile motor. In order to determine the allowable debonded depth in different storage period, a method to analyze the stability of the interfacial crack is presented. Under the circumstance of internal pressure and axial acceleration loading, the three-dimension finite element models of the motor grain with interfacial debonded cracks were established, and several interfacial debonded cracks were preset along the stress relief boot between cladding and propellant. Thus three-dimension singular crack elements at the tips of fore and rear stress relief boot were established to simulate the debond propagation. Along with the interfacial debonded crack propagation, the stress intensity factors of the crack tips in different storage period were respectively calculated to prejudge its stability. The method and conclusions will be helpful in using solid missile motor with interfacial debonded cracks.]]></description>
<pubDate>2013/3/14 0:00:00</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[YUAN Duancai,LEI Yongjun,TANG Guojin and MENG Shangyang]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>YUAN Duancai,LEI Yongjun,TANG Guojin and MENG Shangyang</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200603005]]></guid><cfi:id>699</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Type Optimization of Small Satellite Major Joint Based onStatic and Buckling Analysis]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200603006]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The purpose of this paper is to study the type optimization of small satellite major joint, which is based on static and buckling analysis of honeycomb sandwich plates. Firstly the 3-D FEM model of honeycomb sandwich plates was established by the sandwich plate theory, in which the fork-form or faceplate major joint was buried beforehand. After the liner static and buckling analysis, the maximal Von-Mises stress and buckling load were obtained. Compared with the result of experiment, the failure causation to the Honeycomb Sandwich Plates was then determined. Finally the influence of the structural parameters upon load capacity was discussed, and the optimum major joint type was ascertained.]]></description>
<pubDate>2013/3/14 10:38:48</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LI Enqi,LI Daokui,TANG Guojin and LEI Yongjun]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LI Enqi,LI Daokui,TANG Guojin and LEI Yongjun</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200603006]]></guid><cfi:id>698</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Theoretical Modeling and Analysis of the Formation Process ofShaped Charge Jet]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200603007]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The formation process of shaped charge jet was analyzed and the models of all the phases in the formation process were proposed. The detonation of explosive, the interaction of the explosive with the metal liner, the collapse of the liner, and the formation of the jet and slug were taken into account in the models. A calculation of a specified shaped charge was conducted on the basis of the model, and the results conformed to the data from experiment. It shows that the collapse velocity of the peak and the bottom of liner is smaller than that of the middle of liner and therefore the reverse velocity gradient is formed. It can be concluded that the models can be used in the engineering design of MWS and the calculation of penetration parameters.]]></description>
<pubDate>2013/3/14 10:38:48</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[ZHENG Pingtai,YANG Tao and QIN Zizeng]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>ZHENG Pingtai,YANG Tao and QIN Zizeng</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200603007]]></guid><cfi:id>697</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Reveal the Flame Structure of Supersonic CombustionUsing OH-PLIF Technology]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200602001]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Planar laser induced hydroxyl fluorescence (OH-PLIF) technology has been used to image the hydroxyl of supersonic combustion supplied by the hydrogen fuel being ejected to the mach 1.72 freestream in the three different streamwise sections. Employing a frequency-doubled dye laser with wavelength of 283.553nm as exciting laser，the fluorescence intensity of hydroxyl is nearly indirect proportion to the mole fraction of hydroxyl. The highly turbulent flame structure of supersonic combustion has been revealed from the instantaneous PLIF images of hydroxyl. The steady combustion in the cavity can offer on-duty flame stimulating and stabilizing the supersonic combustion. The flame spreads in the radial direction as well as in the stream direction. Having bigger spreading scale of the cavity, the streamwise flame region would diminish a little.]]></description>
<pubDate>2013/3/14 10:38:33</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[GENG Hui,ZHAI Zhenchen,SANG Yan,LIN Zhiyong and ZHOU Jin]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>GENG Hui,ZHAI Zhenchen,SANG Yan,LIN Zhiyong and ZHOU Jin</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200602001]]></guid><cfi:id>696</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Bang-Bang Control for Maintenance and Reconfigurationof Spacecraft Formation Flying]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200602002]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In this paper, the enabling technique of maintenance and reconfigurati on control of spacecraft formation flying is studied. First, the state transfer matrix of relative motion was introduced and the expression of relative motion with constant thrust control was educed. Then, 3 models of thrust were illustrated, which are impulse thrust, continuous thrust and Bang-Bang thrust. With the state transfer matrix, the differences of the thrust models in relative motion control were explored. Results show that in first order means the relative motion control effects with impulse thrust, continuous thrust and Bang-Bang thrust control are equivalent. So the problem of maintenance and reconfiguration of spacecraft formation flying could be implemented with Bang-Bang thrust control.]]></description>
<pubDate>2013/3/14 10:38:33</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[MENG Yunhe and DAI Jinhai]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>MENG Yunhe and DAI Jinhai</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200602002]]></guid><cfi:id>695</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Study of the Automatic Differentiation Method for CalculatingSensitivities in the MDO of Flying Vehicles]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200602003]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The automatic differentiation method (ADM) for calculating sensitivities is presented. It is a powerful method for dealing with the system sensitivity analysis of the multidisciplinary design optimization. The theory of this method, a general procedure for the implementation of this method, and the realization in Visual C++ 6.0 of this method were described in detail. Also there is a comparison between the finite differences method (FDM) and complex variable method (CVM) in this paper. The ADM is shown to have some advantages over the others, thus having the potential to be widely used in the future.]]></description>
<pubDate>2013/3/14 10:38:33</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[YAN Li,CHEN Xiaoqian and WANG Zhenguo]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>YAN Li,CHEN Xiaoqian and WANG Zhenguo</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200602003]]></guid><cfi:id>694</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Simulation of the Flowfield in Secondary Injection VectorControl Nozzle for Solid Rocket Motor]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200602005]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The complex inner flow-field of secondary gas injection for Solid Rocket Motor was numerically investigated by using three-dimensional average Favre equations and the  turbulent models. Three-order spatial scheme and Implicit point Jacobi algorithm were used to solve these equations. It gained the structures of shockwave series of secondary gas injection vector nozzle and complex main/secondary flow image by numerical simulation. The secondary flow field includes complex vortices and shockwave series. It also has interaction by the boundary layer and shockwave, free shearing layer, shockwave, rarefaction wave and heavy gauge separation. The numerical simulation also indicates that secondary hot gas injection results in high temperature on the surface wall round the injector hole. Corresponding thermal protections should be adopted.]]></description>
<pubDate>2013/3/14 10:38:33</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[WU Xiong and ZHANG Weihua]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>WU Xiong and ZHANG Weihua</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200602005]]></guid><cfi:id>693</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Optimization Research on Aerodynamic Figure of the BoxCar under Crosswinds]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200602006]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Under strong crosswinds, the aerodynamic performance of box car is the worst in the universal vehicles used in the railroad. Using 2D, steady state incompressible Navier-Stokes equation and two equations k-εturbulent model for the box car under strong crosswinds, the optimization of the aerodynamic figure has been  carried out by finite volume. Results obtained show that the figure of roof greatly affects the aerodynamic performance of box car. The P<sub>65</sub> box car with arch roof has better aerodynamic performance than the P<sub>64</sub> box car with slope roof. If the roof arc and the lateral wall could be connected by the round fillet, the aerodynamic performance would be much better. With a consideration of the two factors of aerodynamic performance and the effective volume, it is suggested that the roof arc radius should be 2692mm and the fillet arc radius be 500mm.]]></description>
<pubDate>2013/3/14 10:38:33</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LIANG Xifeng<sup>1</sup>,XIONG Xiaohui<sup>1</sup> and YI Shihe<sup>2</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LIANG Xifeng<sup>1</sup>,XIONG Xiaohui<sup>1</sup> and YI Shihe<sup>2</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200602006]]></guid><cfi:id>692</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Trajectory，Solid Rocket and System Integration Design andOptimization of a Rocket with Two Boosters]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200601001]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Considering the mutually interacting phenomenon of such aspects as trajectory, solid rocket motor and system, a set of mathematical analytical models for the design and optimization of rocket were developed. An optimizing calculation with 6 design parameters for the rocket was made by using genetic algorithm. It shows that the optimized concept reduced 17.7% of the booster mass of the primary, indicating that the optimized results are satisfactory.]]></description>
<pubDate>2013/3/25 4:43:30</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[MA Jiaqing,SUN Pizhong,XIA Zhixun and ZHOU Jin]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>MA Jiaqing,SUN Pizhong,XIA Zhixun and ZHOU Jin</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200601001]]></guid><cfi:id>691</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Meso-scale Hot-spot Model of Crack Friction in Solid Propellant]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200601002]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The study was conducted to investigate how the hot-spot formation was caused by crack friction in composite solid propellant under mechanic impact. It was concentrated on processes of crack surfaces slip, crack growth and friction heating of closed crack driven by sheer stress, heat conduction, decomposition of solid propellant and its interaction with the gas-phase product. In view of the fracture mechanics, heat conduction and dynamics of thermal decomposition of solid propellant, the meso-scale hot-spot model of crack friction was established. By making numerical calculation of the model, the process and condition for hot-spot formation were discussed, from which it is concluded that friction between crack surfaces slip and crack growth can lead to formation of hot-spot in composite solid propellant.]]></description>
<pubDate>2013/3/25 4:43:31</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[CHEN Guangnan<sup>1</sup>,ZHANG Weihua<sup>1</sup>,LIU Ziru<sup>2</sup> and WANG Ningfei<sup>2</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>CHEN Guangnan<sup>1</sup>,ZHANG Weihua<sup>1</sup>,LIU Ziru<sup>2</sup> and WANG Ningfei<sup>2</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200601002]]></guid><cfi:id>690</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Stability of Baselines of Spaceborne InSAR in EvenPhase Configurations]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200601003]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Spaceborne InSAR (Interferometri Synthetic Aperture Radar), whose baselines may undergo complicated variations while the satellite formation flies in the space, is widely used in earth observation. Based on the principle of satellite formation, the even phase configuration for the spaceborne InSAR was defined. Then baselines and their stability were supplied from the principle of InSAR measurement, and the stability of spaceborne InSAR in different even phase configurations was addressed.]]></description>
<pubDate>2013/3/25 4:43:32</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LIU Lei and XI Xiaoning]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LIU Lei and XI Xiaoning</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200601003]]></guid><cfi:id>689</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Periodic-relative Rotating Orbits Design for SpacecraftFormations by Numerical Optimization]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200601004]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[It is of great necessity for the long term relative motion of formation flying to choose initial conditions and design the nature-periodic-relative rotating obits with the reference orbit eccentricity and the nonlinear relative motions. It is recognized that it yields considerable errors and is insufficient to employ Hill equations in choosing initial conditions and designing formation flying orbits without fuel consumption. With a consideration of the effects resulting from the reference orbit eccentricity and the nonlinearity relative motion, the numerical optimal technology was utilized in the present study. Results of numerical optimization can be used to determine the invariant-periodic-relative rotating conditions, thus gaining a good insight into formation flying. Numerical simulations demonstrate the correctness and effectiveness of the optimaized results.]]></description>
<pubDate>2013/3/25 4:43:33</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[XING Jianjun,LI Haiyang,TANG Guojin and XI Xiaoning]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>XING Jianjun,LI Haiyang,TANG Guojin and XI Xiaoning</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200601004]]></guid><cfi:id>688</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Efficient Simulation Procedures for Stochastic Analysis ofNonlinear Dynamical Systems]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200601026]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[An efficient simulation procedure for stochastic analysis of nonlinear dynamical systems with multi-degree freedom based on Monte Carlo simulation (MCS) is presented. A simple criterion was established for indicating the importance of each dynamical response sample. According to this criterion, Russian Roulette and Split (RRS) method was applied to deal with the selected samples. The efficiency of this algorithm was much higher than that of direct MCS while the number of response samples in the low probability regions was increased. The result of evaluated examples demonstrates that the methodology presented in this paper has the advantage of being simple in operation, thus applicable to realistic engineering calculation.]]></description>
<pubDate>2013/3/25 4:43:54</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[ZHANG Shujun and REN Junguo]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>ZHANG Shujun and REN Junguo</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200601026]]></guid><cfi:id>687</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[The Residual Stress Intensity Factor of Surface Cracks ina Thick Plate with Butt Joints]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200706001]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The paper presents an approach to deal with residual stress intensity factors for surface cracks in a thick plate with butt joints by using line-spring model. Based on the Reissner's plate theory along with continuously distributed dislocation thought, the problem of the thick plate with butt joints is treated with a set of Cauchy-type singular equations, which are resolved by Gauss-Chebyshev method. The numerical results of the present method for the surface crack are compared with those of finite element method, and the compared results show good agreement. It is indicated that the line-spring model is not only reasonable and viable for surface cracks analysis in residual stress fields, but simple and convenience for engineering application.]]></description>
<pubDate>2013/2/28 5:09:21</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[YUAN Jiehong and DUAN Jingbo]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>YUAN Jiehong and DUAN Jingbo</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200706001]]></guid><cfi:id>686</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Shock Impinge on Supersonic Cross Flow Injection]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200706002]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[To investigate the shock impingement on vertical injection in supersonic flow, shock was produced by a 9mm long, 23° angle wedge. The images of shocks impinged at different position and pressure of gas and liquid injection were achieved by using both a high speed camera and a schlieren system. Results revealed that gas and liquid injection almost have similar phenomena, that is, impinged by the shock, fuel turbulent intensity will increase, fuel distribution area will be larger in supersonic flow, spreading more quickly into the main supersonic flow, and the shock impinged at the foreside affect more than rearward of injection.]]></description>
<pubDate>2013/2/28 5:09:21</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[PAN Yu and WANG Zhenguo]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>PAN Yu and WANG Zhenguo</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200706002]]></guid><cfi:id>685</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Shape Design and Analysis of Hypersonic Forebody Side Edges]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200706003]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Aerodynamic characteristics of fore-bodies deduced simply from 2D configurations were studied. To restrain the compressed flow from spilling at side edges of forebodies, shaped waverider was added to the fore-body sides and features of the new fore-body as waverider were proven by CFD analysis. More discussion about volume efficiency of the new shape was made and a concept as usable volume efficiency was presented. Different shapes side edges were designed, usable volume efficiency of each shape was discussed together with aerodynamic characteristics.]]></description>
<pubDate>2013/2/28 5:09:21</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LI Xiaoyu,PAN Sha,LI Hua and DING Guohao]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LI Xiaoyu,PAN Sha,LI Hua and DING Guohao</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200706003]]></guid><cfi:id>684</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Bayesian Linear Calibrated Prediction Approach in WarheadVirtual Experiment]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200706004]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The shaped charge penetration performance is sensitive to material model parameters of armor plate in virtual experiment. A Bayesian linear calibrated approach was proposed to obtain precise prediction of penetration limit. Statistical relationship between the physical process, the computer model output and experiment observations was formulated, combined with calibration experiment observations, to estimate the unknown model parameter. Analysis of an example demonstrates that the proposed approach is efficient in large calibration problem involving various uncertainties.]]></description>
<pubDate>2013/2/28 0:00:00</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[JIANG Zhenyu and ZHANG Weihua]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>JIANG Zhenyu and ZHANG Weihua</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200706004]]></guid><cfi:id>683</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Numerical Simulation of Dynamic Flow Field in BoosterDetaching Process]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200706005]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The 3D N-S equations are numerically solved, while NND2M scheme is used for the discretization of the equations, aimed to simulate the dynamic flow about the process in which booster takes apart from upper stage. The effect that the jet of the counter-thrust rocket motor exerts on the axial force on the base of upper stage body is analyzed. The results of the simulation show a law that counter-thrust rocket jet has a great effect on the upper stage body while the distance between them is short, which produces a big axial force doing harm to the flight stability of upper stage.]]></description>
<pubDate>2013/2/28 5:09:21</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[MA Jaqing,LIU Jun and ZHOU Jin]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>MA Jaqing,LIU Jun and ZHOU Jin</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200706005]]></guid><cfi:id>682</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Study on Bayesian Belief Network Method for Engine Tests Sensor Data Validation]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200706024]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[A method for fusing evidence information using Bayesian belief network is introduced for sensor data validation. Uncertainty expression and inference mechanism of sensor states and relations in engine and its components test are defined. The algorithms for automatic generation of the Bayesian belief network files, belief probability calculation and network update are developed. The methodology is demonstrated and validated in a model rocket engine.]]></description>
<pubDate>2013/2/28 5:09:22</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[TANG Yajuan and ZHANG Weihua]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>TANG Yajuan and ZHANG Weihua</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200706024]]></guid><cfi:id>681</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Experimental Study of the Configuration Optimizationof Scramjet Combustor]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200705001]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[An experimental study was conducted on the direct-connect scramjet combustor experiment system to investigate the performance optimization of scramjet combustor by adjusting the shape angles and fuel injection. An orthogonal array design of experiment method was used to organize the combination of shape angles. For every combination of shape angles, five experiments with different fuel injection arrangement were carried out, and every experiment was actualized with three equivalence ratios by adjusting a throttling venturi. The test data were used to build a response surface model of the combustor performance with respect to configuration parameters for combustor configuration optimization. The optimal combustor configuration was obtained by two successive optimizations, and the effects of configuration parameters on combustor performance were analyzed. The results showed that the thrust gain of optimal combustor configuration was increased by 10.4% relative to the baseline configuration, and the combustor performance was influenced strongly by the couple of configuration parameters.]]></description>
<pubDate>2013/2/28 5:09:08</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[WU Xianyu,LI Xiaoshan,DING Meng,LIU Weidong and WANG Zhenguo]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>WU Xianyu,LI Xiaoshan,DING Meng,LIU Weidong and WANG Zhenguo</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200705001]]></guid><cfi:id>680</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Experimental Investigation on Pressure Matching of Multi-nozzleSupersonic Ejector]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200705002]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[An ejector test facility was established to investigate the multi-nozzle supersonic ejector performance, and hot rocket exhaust gases were used as primary and secondary driving fluids. Emphases were placed on pressure matching between primary and secondary flows. The investigation indicates that the higher the total pressure of primary flow is and the lower the static pressure of on primary nozzle exit is, the more convenient it is for the performance to match with the secondary flow, and that the lower the secondary flow total pressure is, the more the critical ejector performance is required to maintain pressure matching, and that the secondary flow total temperature has little influence on pressure matching.]]></description>
<pubDate>2013/2/28 5:09:08</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[WU Jiping,CHEN Jian and WANG Zhenguo]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>WU Jiping,CHEN Jian and WANG Zhenguo</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200705002]]></guid><cfi:id>679</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Implementation of Real-time Fault Detection Algorithms Basedon Neural Network  for Liquid Propellant Rocket Engines]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200705003]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Based on the back propagation and radial basis function neural network, and using the tool of Matlab and Lab Windows/CVI, the real-time fault detection algorithms for the start-up and main-stage process of a certain liquid-propellant rocket engine in ground tests are developed in this paper. The algorithms realized were verified with a great deal of historical test-data and also validated in the practical ground tests of the engine. The results show that the algorithms not only can detect the fault of the engine in time and efficiently without false alarm and missing alarm, but also can meet the real-time ability and robustness requirement.]]></description>
<pubDate>2013/2/28 5:09:08</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[HUANG Qiang,WU Jianjun,LIU Honggang and XIE Tingfeng]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>HUANG Qiang,WU Jianjun,LIU Honggang and XIE Tingfeng</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200705003]]></guid><cfi:id>678</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[One-dimensional Numerical Simulation of Magnetohydrodynamicfor Pulsed Plasma Thruster]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200705004]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[By way of Coupling the effects among the electric field, magnetic field and flow field in the pulsed plasma thruster, the process of the capacitor discharge, propellant ablation and plasma acceleration are characterized, and a one-dimensional time-dependent model based magnetohydrodynamic（MHD）for PPT is presented in this paper. The simulation results are analyzed and compared with the experiment. The result exhibits that the model perfectly reveals the thruster discharge process, variation of ablated mass and surface temperature of propellant.]]></description>
<pubDate>2013/2/28 5:09:08</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[YANG le,ZHOU Jin,YIN Le,WU jianjun and SHI Jie]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>YANG le,ZHOU Jin,YIN Le,WU jianjun and SHI Jie</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200705004]]></guid><cfi:id>677</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[An Improved Fitting Algorithm Design of BroadcastEphemeris for GEO Satellite]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200705005]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[An improved fitting algorithm of Broadcast Ephemeris for GEO satellite with near-zero-inclination is introduced in the paper. The main idea of the algorithm requires the appropriate rotation of the coordinate reference plane to the position observations based on the general algorithm. Within the algorithm, in particularly, the corresponding coordinate transformation to the fitting initial value is proposed. According to the method, fitting problem in the correlation of orbital parameters can be resolved, and the convergence of iterations is quickly achieved. Meanwhile, the computation for the user receiver is simplified. The simulation results show that the Root-Mean-Square error reaches centimeter level and the fitting accuracy can be guaranteed, indicating the effectiveness of the method.]]></description>
<pubDate>2013/2/28 5:09:08</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[GAO Yudong,XI Xiaoning and WANG Wei]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>GAO Yudong,XI Xiaoning and WANG Wei</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200705005]]></guid><cfi:id>676</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Research on Low-frequency Oscillation in Hydrogen Peroxide Engine]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200705006]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Hydrogen peroxide is one of the most important directions of liquid rocket propellant. Considering the low-frequency oscillation phenomenon which occurs in experiment of hydrogen peroxide engine, simulation and analysis of the phenomenon based on the propulsion system models were made, and a stable engine was achieved. The current research is helpful for linking system simulation to experiment in hydrogen peroxide engine development.]]></description>
<pubDate>2013/2/28 5:09:08</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LIU Jinghua,TAN Jianguo,YANG Tao and WANG Zhenguo]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LIU Jinghua,TAN Jianguo,YANG Tao and WANG Zhenguo</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200705006]]></guid><cfi:id>675</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Fault Diagnosis of Liquid Rocket Engine  by Dynamic TimeWarping Combined with Decision Tree Method]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200704001]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Through dynamic time warping analysis to the hot-fire test data and simulated fault data of a certain liquid rocket engine, the warped path sets were obtained. Combined with the decision tree method, fault detection and diagnosis were carried out. Results show that there were no failing report and no misstatement for fault tests, and no misstatement for normal tests. Compared with those results by ANN and SVM methods, the successful application of the dynamic time warping method combined with decision tree was proved.]]></description>
<pubDate>2013/2/28 5:08:52</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[HU Xiaoping,HAN Quandong and LI Jinghao]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>HU Xiaoping,HAN Quandong and LI Jinghao</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200704001]]></guid><cfi:id>674</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Trajectories Analyse for Hypersonic Vehicle with ScramjetBased on Perturbation Atmosphere Model]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200704002]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Hypersonic vehicle with scramjet is a new kind of vehicle with bright future. With a  study of its standard trajectories in half-velocity coordinate system, the fly velocity and design parameters were found to be the main factors to influence its skipping trajectories. The trajectory simulations in perturbation and standard atmosphere models showed that change of atmosphere parameters could influence the height, maximal load, maximal heat and total heat of trajectories. These factors should be considered while studying the vehicle design parameters, structure parameters, heat shield system and guide navigate and control (GN&C) system.]]></description>
<pubDate>2013/2/28 5:08:52</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LI Jian,HOU Zhongxi,LIU Xinjian and ZHOU Bozhao]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LI Jian,HOU Zhongxi,LIU Xinjian and ZHOU Bozhao</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200704002]]></guid><cfi:id>673</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Optimized Design and Analyze of Osculating Cone Waverider]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200704003]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Osculating cone waverider configuration is an important design reference to the powered hypersonic vehicle. This paper parameterized the design process of OC waverider and engineering method was used to evaluate waverider's aerodynamic performances. Based on the orthogonal experiment, L/D ratio, volume and volume efficiency were chosen as optimized objective functions to optimize the configuration. CFD simulation shows that the optimized configuration has better L/D, volume, volume efficiency and uniform flow at the base, thus it is an important design reference in the hypersonic engine-airframe integration design.]]></description>
<pubDate>2013/2/28 5:08:52</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[CHEN Xiaoqing,HOU Zhongxi,HE Lietang and LIU Jun]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>CHEN Xiaoqing,HOU Zhongxi,HE Lietang and LIU Jun</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200704003]]></guid><cfi:id>672</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Aerodynamic Configuration of Trans-atmospheric VehicleBased on Waverider Research]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200704004]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[This article researched the aerodynamic configuration design of the glide/skip trans-atmospheric vehicle(TAV) based on waverider with high lift-to-drag ratio. Firstly, design methods of waverider configuration were put forward, and the waverider shape changed from design parameters was fully investigated. Then, the performances of the optimized waveriders under the varieties of Mach number and differed optimization aims were compared and studied. Finally, a TAV configuration with high L-D ratio and high volumetric efficiency was obtained. The conclusion has important reference value to the research of TAV configuration and waverider.]]></description>
<pubDate>2013/2/28 5:08:52</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[HE  Lietang,ZHOU  Bozhao and CHEN  Lei]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>HE  Lietang,ZHOU  Bozhao and CHEN  Lei</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200704004]]></guid><cfi:id>671</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Dynamic Analysis of Passive Constrained Layer Damping Beam withRandomness of Viscoelastic Material]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200704005]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[A dynamic analysis of the passive constrained layer damping (PCLD) beam considering randomness of viscoelastic damping layer was studied by using the transfer function method. With an introduction of the state vector, the governing equation of the PCLD beam in state space was established from the six-order differential motion equation，which was derived by using the Hamilton principle. The closed-form solutions of natural frequencies and loss factors of a PCLD beam were obtained by the distributed parameter transfer function method. The parameters in fractional derivative model of viscoelastic material were regarded as the base random variables, which follow normal distribution in this analysis. The influence of parameter randomness on the natural frequency and the mode loss factor of the structure were analyzed by using the Monte Carlo method. Numerical examples show that the randomness has obvious effects on the correlation coefficient of dynamic characteristic, and the maximal value of the loss factor's correlation coefficient is about 4.5 times as much as the one of material parameter. So it is necessary to carry out the random analysis for PCLD structures.]]></description>
<pubDate>2013/2/28 5:08:52</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LI Enqi,LEI Yongjun,LI Jiutian,LI Daokui and TANG Guojin]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LI Enqi,LEI Yongjun,LI Jiutian,LI Daokui and TANG Guojin</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200704005]]></guid><cfi:id>670</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Creditability Theory-based Analysis for Terminal Divert Ability ofStandard Missile-3]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200704008]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The analysis of the terminal divert ability of SM-3 is put forward based on the creditability theory. The expression of the maximal zero effort miss which could be corrected by SM-3 during the terminal course was deduced based on relative motion dynamics. Creditability theory was used for modeling the fuzzy parameters in the expression, and fuzzy simulation was adopted to obtain the possibility measured pessimism value and optimism value, creditability measured mean value and normalized variance, and its distribution functions of possibility, necessity and creditability. The research could supply a theoretical support for the motor design of midcourse maneuvering penetration of a ballistic missile, and supply an effective way for get reasonable unknown information from limited known information.]]></description>
<pubDate>2013/2/28 5:08:53</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[WU Qixing,LI Xiaobin and ZHANG Weihua]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>WU Qixing,LI Xiaobin and ZHANG Weihua</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200704008]]></guid><cfi:id>669</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Experimental Investigation on Supersonic Flows over Cavities]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200703001]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Characteristics of supersonic cold flows over cavities were investigated experimentally and numerically, and the effects of cavities of different sizes on supersonic flow field were also analyzed. Results indicate that cavity flow structure has little relevance to L/D within the range of 5～9, and the ramp angle of the rear wall will not alter the overall structure of the cavity flow within the range of 300～600, but it can alter the development of the shear layer and the structure of the circumfluence in cavities.]]></description>
<pubDate>2013/2/28 5:08:40</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[FANG Tianwen,DING Meng and ZHOU Jin]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>FANG Tianwen,DING Meng and ZHOU Jin</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200703001]]></guid><cfi:id>668</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[An Investigation of Lightcraft Launching Task Design andOptimum Parameter Analysis Based on Laser Propulsion]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200703003]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In order to launch objects into low-earth circular orbit using an earth-based laser and a lightcraft with 100kg initial mass, the relationships among the concerned parameters such as the laser average power, the characteristics of laser propagation in atmosphere, light receiver size of lightcraft，the specific impulse of engine, and the energy conversion efficiency of engine were investigated. Meanwhile, the optimal trajectory for such a task was also studied. The necessary average laser power was estimated from the initial acceleration of the lightcraft. The minimum size of the lightcraft's light receiver was derived from laser range. Based on the flight dynamic model of lightcraft and the estimated parameters, the optimum trajectory from the ground to low-earth orbit was computed. The results show that the maximum mass-to-orbit is up to 35.5kg, and the optimum specific impulse is 8140m/s.]]></description>
<pubDate>2013/2/28 5:08:40</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[HE Zhen and WU Jianjun]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>HE Zhen and WU Jianjun</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200703003]]></guid><cfi:id>667</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Free Vibration and Stability of Multiple-step Beams under SteppedAxial Pressure by Distributed Transfer Function Method]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200702001]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[With the distributed transfer function method, a closed-form solution is obtained for free vibration and stability of a multiple-step beam under stepped axial pressures. According to variations of the geometry of the cross-section, the material and the axial pressure in axial direction, the beam is divided into multiple sub-beams whose closed-form solution is obtained with the distributed transfer function method. The natural frequencies and buckling loads along with their mode shapes are obtained by using the displacement continuity conditions and force balance conditions between the sub-beams. The method was validated through numerical examples of three-step beams. The natural frequencies of multiple-step beams under different axial pressure in each section were calculated with the example of four-step beams.]]></description>
<pubDate>2013/2/28 5:08:27</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LI Daokui,LEI Yongjun and TANG Guojin]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LI Daokui,LEI Yongjun and TANG Guojin</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200702001]]></guid><cfi:id>666</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Agent-based Autonomous Formation Reconfiguration Techniquesfor Distributed Satellite Systems]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200702002]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The autonomous formation reconfiguration of Distributed Satellite Systems is one of the typical missions of autonomous control. Formation reconfiguration of distributed satellites was divided into two aspects: relative orbit control and overall planning.  Furthermore, a uniform description of formation reconfiguration was presented. Then the problem of Agent-based autonomous formation reconfiguration was discussed in the hierarchical control architecture of distributed satellites, and the implementation framework in ObjectAgent is introduced. A novel spiral control scheme was raised for relative orbit regulation, and the cost budget was estimated. Auctioneering algorithm was adopted for position allocation. Simulation results show the effectiveness of Agent-based autonomous formation reconfiguration.]]></description>
<pubDate>2013/2/28 5:08:27</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[ZHANG Jian and DAI Jinhai]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>ZHANG Jian and DAI Jinhai</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200702002]]></guid><cfi:id>665</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Flight Performance Analysis of the Solid Fuel Ramjet]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200702003]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The solid fuel ramjet is related to the missile flight conditions through the inlet. Compared with other kinds of ramjet, the marked characteristic of the solid fuel ramjet is that its propellant combustion chamber process is not only concerned with the propellant composition, motor structure and combustion pressure, but also dependent on the air parameter in the combustion air inlet. Hence, the operation process is rather complex. The operation process simulation model, the first of its kind in China, was established, and the effect of the missile flight mach number and height on the motor performance was discussed.]]></description>
<pubDate>2013/2/28 5:08:27</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[GUO Jian,ZHANG Weihua and XIA Zhixun]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>GUO Jian,ZHANG Weihua and XIA Zhixun</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200702003]]></guid><cfi:id>664</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Theoretic and Experimental Research onPressure-adaptive and Flux-constant Orifice]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200702004]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Under the severe demand of the Water/Metal Fuel Motor on the flux of water in the starting period, a new type of pressure-adaptiveand flux-constant orifice was brought forward. The flux-constant principle of this orifice with pressure-adaptability was analyzed theoretically. Experiments were carried out. Their results show that the orifice can satisfactorily adjust the flux resistance automatically and keep the flux constant.]]></description>
<pubDate>2013/2/28 5:08:27</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LI Fang,WANG Zhongwei and ZHANG Weihua]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LI Fang,WANG Zhongwei and ZHANG Weihua</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200702004]]></guid><cfi:id>663</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Tightly Coupled Integration Technology of RDSS Time DifferenceCarrier Phase/SINS and Its Experimental Research]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200702005]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The shortcomings of active positioning mode of Chinese Beidou navigation satellites system are introduced while a new technology is proposed on the basis of time difference carrier phase (TDCP) for RDSS/SINS tightly coupled integration. The TDCP measurements are used as the observation of Kalman filter to establish a tightly coupled integrated navigation system that works in passive mode. The principles and mathematic model of TDCP are described and a Kalman filter for integration is designed. Static and dynamic state tests were performed to validate the algorithm and evaluate the accuracy. The results show that the accumulation of velocity errors and position errors are attenuated remarkably.]]></description>
<pubDate>2013/2/28 5:08:27</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[TANG Yonggang,LIAN Junxiang,WU Wenqi and HU Xiaoping]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>TANG Yonggang,LIAN Junxiang,WU Wenqi and HU Xiaoping</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200702005]]></guid><cfi:id>662</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Numerical Simulation for the Fuel Jetand Inner Flowfield of Scramjet Combustion Chamber]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200702006]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The inner flow field of scramjet combustion chamber with fuel jet and cavity structure was simulated numerically on the basis of the 3 D Navier Stokes equations. Finite differential method was used. With a  comparison between the numerical and experimental results, the unsteadiness of fuel jet and influence of cavity structure on the flow field were discussed. From the results, it is observed that the stable flow field of numerical simulation is similar to experimentation, and the unsteady dynamic phenomenon that fuel jet moves downstream and diffuses into the cavity is captured from simulation.]]></description>
<pubDate>2013/2/28 5:08:27</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[ZHOU Songbai,LIU Jun,GUO Zheng,WANG Wei and GENG Hui]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>ZHOU Songbai,LIU Jun,GUO Zheng,WANG Wei and GENG Hui</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200702006]]></guid><cfi:id>661</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Modular Model of Space Propulsion Systemin the Whole Operation Process]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200702007]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[This paper established dynamic mathematical models of simulation modules of the space propulsion system in the whole operation process, which include liquid pipeline module, triple link module, filling in pipeline module, thrust chamber module and so on. The lumped parameters method is employed, aiming at synchronously considering the inertia, viscosity and compressibility of liquid. Thus the ordinary differential equation set built in the research can generally reflect the distributed characteristics of the operation process in the supplying system.]]></description>
<pubDate>2013/2/28 5:08:27</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[FAN Zhongze<sup>1</sup>,HUANG Minchao<sup>2</sup>,YU Yong<sup>3</sup> and ZHU Hengwei<sup>3</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>FAN Zhongze<sup>1</sup>,HUANG Minchao<sup>2</sup>,YU Yong<sup>3</sup> and ZHU Hengwei<sup>3</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200702007]]></guid><cfi:id>660</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[An Analytic Solution for the V-bar Departure Controlunder the Field of View Constraint]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200702009]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[By the analytic method, the control of V-bar departure in rendezvous and docking under the field of view constraint was studied. The basic maneuver strategy of V-bar departure using radial impulse was described. This strategy fulfils the requirement of minimum plume impact on the target and trajectory safety. The analytic solution calculating the maximum field of view using radial impulse and calculating the permitted impulse using field of view was developed on the basis of CW equation while the solution with the formulas to calculate the time of the maximum field of view and the departure distance in the V-bar direction was also developed. Finally, the comparison between numerical and analytic method shows the method developed in this paper is correct.]]></description>
<pubDate>2013/2/28 5:08:27</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[WANG Hua,TANG Guojin and LI Haiyang]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>WANG Hua,TANG Guojin and LI Haiyang</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200702009]]></guid><cfi:id>659</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[The Effect of TT&C Deployment on the Regional SatelliteNavigation System]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200701001]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The telemetry, tracking, and command (TT&C) network is one of the key issues for  regional navigation satellite system. Firstly, the domestic deployment of TT&C stations was discussed. The observability on navigation satellite constellation based on domestic stations was analyzed by means of grid computation. Then, the observing geometric structure intension on satellites was synthesized by the position dilution of precision (PDOP), and the influence of the station's location on satellite orbit determination precision was valuated by the condition number of normal matrix. The simulation shows that the TT&C stations located in the limited span of Chinese territory and the existing TT&C resources can accomplish the TT&C task. Finally, the setting of stations abroad was considered and simulated, and it verified that the joining of the stations abroad, such as the station in Perth in Australia, can improve the observing geometric structure intension and satellite orbit determination precision.]]></description>
<pubDate>2013/2/28 5:08:14</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[WEN Yuanlan<sup>1</sup>,LIU Qixu<sup>2</sup>,ZHU Jun<sup>1</sup> and LIAO Ying<sup>1</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>WEN Yuanlan<sup>1</sup>,LIU Qixu<sup>2</sup>,ZHU Jun<sup>1</sup> and LIAO Ying<sup>1</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200701001]]></guid><cfi:id>658</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[The Technique of the Monitor and Fault Diagnosis of Missile ControlSystem Based on the Bus]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200701002]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[This paper first analyzed the ground test and control system architecture and its characteristics of the missile control system based on the bus. Then it made an explanation to the structure and BIT technique of a single component. Furthermore, it put forward the method of the monitor and fault diagnosis of missile control system based on the bus, in which the formats of bus data interface, the expression of system knowledge and the process of monitor and fault diagnosis were mainly discussed.]]></description>
<pubDate>2013/2/28 5:08:14</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[ZENG Qinghua<sup>1</sup>,DU Mingbo<sup>1</sup>,DU Chengqian<sup>2</sup> and LIU Daoping<sup>1</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>ZENG Qinghua<sup>1</sup>,DU Mingbo<sup>1</sup>,DU Chengqian<sup>2</sup> and LIU Daoping<sup>1</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200701002]]></guid><cfi:id>657</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[The Experimental Research of Shocklet in SupersonicTurbulent Mix Layer]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200701003]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The shocklet was observed based on NPLS techniques in supersonic turbulent mix layer wind tunnel with convective Mach number 1.24. The flow field parameters of mix layer were analyzed with the appearance of shocklet. The method of calculating convective Mach number from experiment image was presented with the consideration that it can avoid unnecessary hypothesis of theory. Finally, the generation and development of shocklet structure were discussed.]]></description>
<pubDate>2013/2/28 5:08:14</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[ZHAO Yuxin,YI Shihe,HE Lin,CHENG Zhongyu and TIAN Lifeng]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>ZHAO Yuxin,YI Shihe,HE Lin,CHENG Zhongyu and TIAN Lifeng</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200701003]]></guid><cfi:id>656</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Simplification of Detailed Reaction Mechanism Based on theSensitivity Analysis and Quasi-steady State Assumption]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200701004]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[A method based on the sensitivity analysis and quasi-steady state assumption was systematically developed in this paper to simplify complex reaction mechanisms. A constant pressure homogeneous reactor model and a detailed reaction mechanism were adopted to calculate the auto-ignition process under the interested condition. Then the result obtained with the detailed mechanism was analyzed through the sensitivity analysis and the redundant species and reactions were identified and deleted from the detailed mechanism to form the skeletal mechanism. After that, the quasi-steady state species (QSSS) which were very small and fast were also found from the skeletal mechanism. The global reaction mechanism was derived with some matrix relations from the skeletal one. Finally, the detailed mechanism GriMech1.2 for methane oxidization was simplified to form skeletal and global mechanism as an example, and the result was validated with a comparison with the one obtained with the detailed mechanism.]]></description>
<pubDate>2013/2/28 5:08:14</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LIN Zhiyong,ZHOU Jin and HUANG Yuhui]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LIN Zhiyong,ZHOU Jin and HUANG Yuhui</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200701004]]></guid><cfi:id>655</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Analysis and Optimization Design of Tetrahedron FormationSpacecrafts in Highly Elliptic Orbits]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200701005]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Several space physics missions that are being designed or flown need spacecrafts flying in a tetrahedron configuration about a highly elliptical reference orbit. At least four spacecrafts can separate space and time, and measure the structural and dynamic parameters of space environment along the mission arc. Based on the orbit element model of relative motion, an analysis was performed to study the influence of four reference orbit elements on the tetrahedron's quality factor and average side length. On the assumption that one spacecraft runs along the reference orbit, a tetrahedron formation optimization design model was proposed, whose design variables are fifteen relative orbit elements of the other three spacecrafts while objective function involves the tetrahedron's quality factor and mean side length. Then, this model is applied in phase I of Magnetosperic MultiScale mission. The results show that a tetrahedron formation with better performance in the mission arc can be found through optimization method while no control is exerted.]]></description>
<pubDate>2013/2/28 5:08:14</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[AN Xueying,XI Xiaoning,ZHANG Weihua and YANG Leping]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>AN Xueying,XI Xiaoning,ZHANG Weihua and YANG Leping</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200701005]]></guid><cfi:id>654</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Comparisons Between Reference-trajectory and Predictor-correctorEntry Guidances for RLVs]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200701006]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[A new reusable launch vehicle (RLV) entry guidance algorithm with ranging technique which only needs to update flight profile parameters was developed and a predictor-corrector entry guidance methodology using Runge-Kutta-Fehlberg method for RLVs combined with trajectory online generation technology was studied. Comparisons between the two guidance schemes were performed, and simulation results show that the two guidance methods are feasible, which indicates that the integration of reference-trajectory entry guidance and predictor-corrector entry guidance is a promising entry guidance scheme for future RLVs.]]></description>
<pubDate>2013/2/28 5:08:14</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[HU Jianxue<sup>1</sup>,CHEN Kejun<sup>1</sup>,ZHAO Hanyuan<sup>1</sup> and YU Menglun<sup>2</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>HU Jianxue<sup>1</sup>,CHEN Kejun<sup>1</sup>,ZHAO Hanyuan<sup>1</sup> and YU Menglun<sup>2</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200701006]]></guid><cfi:id>653</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Direct Adptive Neuro Flight Controller Based on RBF NN]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200701007]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[A flight controller structure based on RBF NN was designed,and its control law and tunned law for RBF NN parameters.(center and width of gauss function, weight) were presented. F8 Fight aircraft was taken as the control object and a simulation was thus performed. The results from simulation show that, even under 70% model error, this controller manifests excellent control performance and good robustness. Fully-tunned law presented in this paper is better than the conventional algorithm which only adjusts weight value of RBF NN.]]></description>
<pubDate>2013/2/28 5:08:14</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[SUN Zhibing and DAI Jinhai]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>SUN Zhibing and DAI Jinhai</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200701007]]></guid><cfi:id>652</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Primary Experimental Study on the Performance of Water-ramjetEngine and the Magnesium-based Fuel]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200701008]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The performance of water-ramjet engine was calculated by the thermodynamic calculation software, then the basic composition of the magnesium-based hydro-reactive metal fuel was determined and the fuel grain was produced. The model water-ramjet engines with the fuel have been tested successfully. The performance of the engine and the attributes of the fuel were investigated primarily.]]></description>
<pubDate>2013/2/28 5:08:14</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LI Shiliang,ZHANG Wei,ZHANG Weihua,YANG Shiqing,ZHU Hui and HE Bo]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LI Shiliang,ZHANG Wei,ZHANG Weihua,YANG Shiqing,ZHU Hui and HE Bo</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200701008]]></guid><cfi:id>651</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Inlet Design and Performance Calculation forRamjet Assisted Projectile]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200806001]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[An inlet has been designed for ramjet assisted range projectile. With the features of ramjet assisted range projectile, such factors as cone parameters, throat parameters, encloser and parameters have been discussed. In particular, an analysis of cone lip parameters and diffuser angle is made. Furthermore, three inlets, single cone with inner contraction, single cone without contraction, and double cone with inner contraction have been designed. With these inlets, numerical simulation and performance also have been conducted. The effect of decisive parameters in inlet design has been analyzed. The result of numerical simulation shows that under the requirement of ramjet assisted range projectile, double cone with inner contraction has better performance.]]></description>
<pubDate>2012/12/7 2:58:05</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LI Li,LIU Wei and YANG Tao]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LI Li,LIU Wei and YANG Tao</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200806001]]></guid><cfi:id>650</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Simulation of Flume of Pulsed Plasma Thrusterby DSMC/PIC Fluid Hybrid Method]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200806002]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[At present, micro satellites and small satellites are under rapid development. The pulsed plasma thruster is a good choice for its propellant system. For space application, the flume is in a great need to be studied. In this paper, DSMC(Direct Simulation Monte Carlo)/PIC (Particle in Cell) fluid hybrid method and one dimension MHD discharge model are used to simulate the NASA Glenn PPT flume from end to end. The distribution of deflection angle at the thruster outlet is achieved by calculation and comparison between experimental results. The results show that the deflection angle at the thruster outlet can improve the diffusion of flume, thus making an important factor influencing the simulation results.]]></description>
<pubDate>2012/12/7 2:58:05</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[YIN Le,ZHOU Jin,YANG Le and LI Ziran]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>YIN Le,ZHOU Jin,YANG Le and LI Ziran</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200806002]]></guid><cfi:id>649</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Study on Satellite Orbit Tracking Data Reprocessingwith Semi-parametric Regression Model and Based on the Wavelet De-noising Approach]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200806003]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Traditionally, the satellite orbit measurement data are reprocessed by least-square polynomial fit method. Because of the non-linear errors in the satellite tracking, the accuracy of data reprocessing is reduced. The current approach, based on the semi-parametric regression model, holds that the observations can be de-noising via wavelet threshold, and the nonlinear errors can be estimated and removed from the observations. The data reprocessing method with semi-parametric regression model based on the wavelet de-nosing approach is proposed to improve the accuracy of data reprocessing. Finally, the simulation of the reprocessing of a united S-band(USB) satellite orbit measurement data showed that the method could separate the white noise and nonlinear errors, and greatly improve the accuracy of data reprocessing.]]></description>
<pubDate>2012/12/7 2:58:05</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[PAN Wanghua<sup>1,2</sup>,WEN Yuanlan<sup>1</sup>,ZHU Jun<sup>1</sup> and LIAO Ying<sup>1</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>PAN Wanghua<sup>1,2</sup>,WEN Yuanlan<sup>1</sup>,ZHU Jun<sup>1</sup> and LIAO Ying<sup>1</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200806003]]></guid><cfi:id>648</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[System Error Calibration for GPS Precise OrbitDetermination with SLR Data]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200806004]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[This paper analyzes the principle of GPS precise orbit determination evaluation with satellite laser ranging (SLR) data, and provides a new method to calibrate orbit system error. In order to calibrate the system error and recognize the orbit precision difference in three axes, the new method uses observation data from several stations in one pass arc, and makes orbit error projection at different time. A certain amount of SLR data must be maintained for the method proposed. The simulation results indicate that using orbit error projection for more than 3 stations at different time in one pass arc can calibrate linear system error, and the bigger the angle between station and satellite vectors is, the more accurate the estimation of the system error is.]]></description>
<pubDate>2012/12/7 2:58:05</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[GU Defeng<sup>1</sup>,TU Xianqin<sup>1,2</sup> and YI Dongyun<sup>1</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>GU Defeng<sup>1</sup>,TU Xianqin<sup>1,2</sup> and YI Dongyun<sup>1</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200806004]]></guid><cfi:id>647</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Rapid Transfer Alignment Based on Large MisalignmentSINS Error Model]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200806005]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[A large misalignment error model of strapdown inertial navigation system(SINS) was deduced for the large relative attitude of rapid transfer alignment existing between the master and slave SINS. The Euler angles were introduced to describe the attitude errors. The Euler's kinematics equations were applied to achieve the accuracy error model. The unscented Kalman filter (UKF) was applied to avoid the derivation calculus of the attitude measurement equations which were complex nonlinear functions. The singular value decomposition (SVD) was used to solve the ill-conditioned problem of covariance matrix. The simulation experiment results show that the alignment accuracy is improved both in small angle uncertainties, and large angle uncertainties.]]></description>
<pubDate>2012/12/7 2:58:05</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[TAN Hongli,HUANG Xinsheng and YUE Dongxue]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>TAN Hongli,HUANG Xinsheng and YUE Dongxue</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200806005]]></guid><cfi:id>646</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Study of Side Window Orientation of Kinetic Kill Vehicle Operating in Higher Atmosphere]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200806008]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[A side window is usually adopted by the kinetic kill vehicle (KKV) operating in higher atmosphere as a basic layout. The engagement result is gravely influenced by the side window orientation which involves many factors. On the basis of some ideal hypothesis, the regularity of the line-of-sight variation rate is investigated, and the effect of the attack angle induced by the orientation is analyzed theoretically. Consequently, the optimal direction of the side window orientation is educed as the aerodynamic force taken into account only. Subsequently, the law to determine the orientation directions at all fighting altitudes are put forward, when the aerodynamic force, the divert  and attitude control system are concerned. The numerical simulation result shows that this method can meet the side window detection command and the KKV only needs one orienting action to finish the interception in most circumstances.]]></description>
<pubDate>2012/12/7 2:58:05</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[ZHANG Hongbo,GUO Zhenyun and TANG Guojian]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>ZHANG Hongbo,GUO Zhenyun and TANG Guojian</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200806008]]></guid><cfi:id>645</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Numerical Simulation of Effect of Attack Angle on the VertexCharacteristics of  Double-Delta Wing]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200805001]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Numerical investigation of the vertex flow characteristics on double-delta wing was presented. The flows over the 76/40-deg double-delta wing were computed with complete laminar when attack angles varies from 5-deg to 30-deg. The flow structures were exhibited in different angles and the analysis of the aero-dynamic characteristics was presented. The investigation shows that vortexes on the double-delta wing surface may fiercely interact with each other and the burst of vortexes caused by large attack angle will exert great influence on the aero-dynamic characteristics of double-delta wing.]]></description>
<pubDate>2013/3/11 3:01:22</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[YANG Xiaoliang and LIU Wei]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>YANG Xiaoliang and LIU Wei</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200805001]]></guid><cfi:id>644</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Engineering Calculation of Heat Flux at the StagnationPoint of Cylinder in Transitional Region]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200805002]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[By the use of linear interpolation and accommodate parameter, a heat transfer bridging relation in transitional region is proposed in this paper, aiming to fix the accommodate parameter for cylinder whose edge surface is windward. The results of the bridging relation were validated by using DSMC method and compared with the results of other bridging relations. The validation shows that the bridging relation can be used to calculate the heat flux at the stagnation point with Mach number larger than 10.]]></description>
<pubDate>2013/3/11 3:01:22</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[RONG Yisheng<sup>1</sup>,CHEN Weifang<sup>2</sup>,SHI Yuzhong<sup>1</sup> and LIU Weiqiang<sup>1</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>RONG Yisheng<sup>1</sup>,CHEN Weifang<sup>2</sup>,SHI Yuzhong<sup>1</sup> and LIU Weiqiang<sup>1</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200805002]]></guid><cfi:id>643</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Theoretical Analysis of Heat and Mass Transfer of Moving Droplet during Evaporation]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200805003]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Theoretical analysis of heat and mass transfer is developed for the unsteady evaporation of a moving droplet which is suddenly placed into the gas circumstances. A mathematical model is proposed for the unsteady evaporation process of a droplet at the first moment and is solved by numerical method. The results indicate that the evaporation rate is very high for a moving droplet suddenly placed into the gas circumstance at the initial moment, which can make the temperature of droplet surface decline. The scope of the temperature decline is concerned with the initial temperature of the droplet, gas circumstances, and the initial velocity of the moving droplet as well.]]></description>
<pubDate>2013/3/11 3:01:22</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[SU Lingyu and LIU Weidong]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>SU Lingyu and LIU Weidong</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200805003]]></guid><cfi:id>642</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Numerical Simulation of the Effect of Viscosity on thePerformance of Hypersonic Vehicle]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200805004]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Two-dimension coupled implicit Navier-Stokes equations and standard k-εviscid model are introduced to simulate the inner and outer flow field of hypersonic vehicle, and the equations are discretized by the second order upwind scheme. When angle of attack is changing from -10°to 7°, the effects of viscosity on the lift, drag force and pitching moment characteristics of hypersonic vehicle in three working conditions including inlet closed, inlet open but unfired, inlet open and fired were discussed. Result shows that the influence is prominent when hypersonic vehicle works under inlet open but unfired、inlet open and fired conditions. especially This case will occur when the drag force characteristic, viscous drag force exceeds 50% of total drag force.]]></description>
<pubDate>2013/3/11 3:01:22</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[HUANG Wei,LIU Jun,LUO Shibin and WANG Zhenguo]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>HUANG Wei,LIU Jun,LUO Shibin and WANG Zhenguo</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200805004]]></guid><cfi:id>641</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Optimized Design and Experimental Study ofWaverider Configuration]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200804001]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Waverider is an important designing reference in the design of hypersonic high L/D vehicle. L/D, volumetric efficiency and volumetric are factors to be considered in the designing process. A parameter design model of cone derived waverider was established in this paper and an improved multi-object Genetic Algorithm was chosen as the optimized algorithm. Lift to Drag ratio, volumetric and volumetric efficiency were chosen as optimized objective functions in the multi-object optimization of the cone derived waverider. The optimized model was designed and experiments of attack state's wind tunnel at KD-01 hypersonic gun wind tunnel were conducted. The experiment results were compared with those of CFD. It shows that the model has good L/D performance and can maintain high L/D at certain angle of attack's scope. The CFD results and experiment results are almost identical. The research result is helpful for the hypersonic glide aircraft's aerodynamic design.]]></description>
<pubDate>2012/12/7 2:57:37</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[XU Shaohua,HOU Zhongxi,CHEN Xiaoqing and XIA Zhixun]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>XU Shaohua,HOU Zhongxi,CHEN Xiaoqing and XIA Zhixun</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200804001]]></guid><cfi:id>640</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[The Shape Optimization Analysis of Solid Motor Star Grain]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200804002]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Structural integrity is one criterion of vital importance for solid motor. It is shown that the optimization of grain shapes and material properties can greatly improve the structural integrity. Owing to particularity of shape optimization, the Basis Vector which guides the optimization procedure is introduced. The auxiliary model which is used to help generate basis vectors is also designed. Based on the characteristics of solid motor and its loads conditions, the plain-strain model of the star is built. Several sensitivity factors of the shape parameters are studied, and the optimal schemes are discussed later. The results obtained will offer guidance to the structural integrity analysis and optimization design for solid motor. The methods and conclusions are beneficial to the designers and manufacturing of solid motor.]]></description>
<pubDate>2012/12/7 0:00:00</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LEI Yongjun<sup>1</sup>,YUAN Duancai<sup>1</sup> and HE Huang<sup>2</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LEI Yongjun<sup>1</sup>,YUAN Duancai<sup>1</sup> and HE Huang<sup>2</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200804002]]></guid><cfi:id>639</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Characteristics of Return Trajectory of Lunar Probe]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200804003]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Mathematical model and characteristic analysis of return trajectory for lunar probe were studied. Firstly, mathematical model of return trajectory was established in 3D space; then some important characteristics were obtained from simulation analysis, especially those characteristics of trajectory escapes from lunar sphere of influence on longitude 80°E costing the least energy; at last an example with a preliminary trajectory and a precise trajectory was proposed, which proves that this analytical method is able to provide initial value for precise design，and the characteristics can guide the actual design.]]></description>
<pubDate>2012/12/7 2:57:37</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[BAI Yuzhu,XI Xiaoning,LIU Lei and WANG Gongbo]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>BAI Yuzhu,XI Xiaoning,LIU Lei and WANG Gongbo</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200804003]]></guid><cfi:id>638</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[A Study on Laser and Plasma Interaction EffectBased on Non-equilibrium Mechanism]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200804004]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The controlled equations based on thermo-chemical non-equilibrium model under the condition of three temperatures were solved numerically by finite difference NND scheme. The inverse bremsstrahlung absorption and plasma resonance absorption were considered when laser transmitted in air plasma. Plasma initiation process was simulated in coupling computation. The mechanism of formation and development of plasma absorbing wave were investigated under different incident laser intensity, while viscidity and diffuseness effects were considered. The results show that the minimum laser intensity needed to form LSD wave based on ZND model is 5.0×10<sup>6</sup> W/cm<sup>2</sup> at the initialized temperature 300K and the pressure is 1atm.]]></description>
<pubDate>2012/12/7 2:57:37</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[YAN Changyu,WU Jianjun,LIU Honggang and HE Zhen]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>YAN Changyu,WU Jianjun,LIU Honggang and HE Zhen</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200804004]]></guid><cfi:id>637</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[A Research on Simulation of Manned Spacecraft Rescueat Low Altitude]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200804005]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In the manned spacecraft rescue at low altitude, the initial conditions of recovery system at parachute-opening point affect obviously cabin safety landing, such as its velocity, altitude and trajectory angle. Similar to the normal return rescue, the process of recovery system rescue at low altitude also has the stages of deployment, inflation, and full-inflation of multilevel parachute. Through applying the recovery system landing dynamic model, and analyzing contrastively the results from simulation, it can be known that the initial altitude from ground of recovery system at parachute-opening point is the first effect factor on the cabin safety landing in rescue at low altitude. In the end, the deceleration process of parachute-opening of multilevel parachute in recovery system is analyzed in detail.]]></description>
<pubDate>2012/12/7 2:57:37</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[GUO Shuwei,DONG Yangbiao,Ding Di and QIN Zizeng]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>GUO Shuwei,DONG Yangbiao,Ding Di and QIN Zizeng</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200804005]]></guid><cfi:id>636</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[A Research of Tether Dynamics in Airship-towed System]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200804006]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[A numerical simulation of dynamical model for some  key dynamics problems of terminal correction submunition is built, using Kane's method which can solve the problem of the Multi-Rigid-body system. Numerical results were validated in the experimentation of airdrop in Airship-towed system. This dynamical model also can be used to solve the problem of Tether dynamics in other fields.]]></description>
<pubDate>2012/12/7 0:00:00</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[TANG Qiangang and WANG Zhenguo]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>TANG Qiangang and WANG Zhenguo</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200804006]]></guid><cfi:id>635</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Experiment and Theoretical Model of High-strengthArmor Normally Penetrated by  Armor-piercing Bullet]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200804007]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The perforation mechanism of the high-strength armor by Armor Piercing Bullet (AP) was investigated by experiments. A theoretical model for the ballistic limit of the armor and residual velocity of the bullet including the effects of the strain rate and the thermal softening of the material was presented. The results show that the theoretical values have fine agreement with those of the experiments. The impact of failure criterion on the results was analyzed and the temperature rising of the shear band and the change rules of energy-dissipating of the target with the input velocities were discussed.]]></description>
<pubDate>2012/12/7 2:57:37</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[YAN Luhui<sup>1,2</sup>,ZENG Shouyi<sup>1</sup> and ZHOU Jianping<sup>2</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>YAN Luhui<sup>1,2</sup>,ZENG Shouyi<sup>1</sup> and ZHOU Jianping<sup>2</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200804007]]></guid><cfi:id>634</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[A Trajectory Generation Strategy Based on Way-points forSpacecraft Relative Motion]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200803001]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[An optimal trajectory generation strategy based on way-points is presented to solve the fixed-time state transition for spacecraft relative motion in a circular orbit. According to the dynamics of relative motion, the optimal transfer trajectory with continuous thrust is investigated by applying optimal control theory. Furthermore，a set of way-points constrained to be along the optimal transfer trajectory are introduced to parameterize the trajectory with impulsive constraints by multi-impulse control. By changing the positions of way-points and the time between two neighboring impulsive burns, the generated trajectory is optimized with quadratic programming algorithm. The simulations show that the strategy is practical and efficient.]]></description>
<pubDate>2012/12/7 2:57:23</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[ZHU Yanwei,YANG Leping and REN Xianhai]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>ZHU Yanwei,YANG Leping and REN Xianhai</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200803001]]></guid><cfi:id>633</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Analysis to the Effects of Mie Scattering in 1.06μmLaser Simulation Tests]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200803002]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Based on the laser signal's emission, propagation and detection during the in-door laser simulation, the effects of the aerosol's Mie scattering is provided for the 1.06μm laser signals. By the construction of the models of the indoor aerosol's scattering, the laser designator's propagation simulation and calculation are carried out. Finally, the discussions related to the arrangement and the methods to reduce the effects of the scattering are delivered in terms of the analysis of and verification by practical measure data.]]></description>
<pubDate>2012/12/7 2:57:23</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LI Hua<sup>1</sup>,QIN Shiqiao<sup>1</sup>,HU Xin<sup>2</sup>,WANG Xingshu<sup>1</sup>,WEI Wenjian<sup>1</sup> and ZHANG Baodong<sup>1</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LI Hua<sup>1</sup>,QIN Shiqiao<sup>1</sup>,HU Xin<sup>2</sup>,WANG Xingshu<sup>1</sup>,WEI Wenjian<sup>1</sup> and ZHANG Baodong<sup>1</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200803002]]></guid><cfi:id>632</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[CFD Analysis for Crossing Shock Wave/TurbulentBoundary Layer Interactions]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200803003]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[A 3d LU-SGS computational code was developed to solve the hypersonic flows, which was modeled by using the compressible three-dimension Reynold averaged Navier-Stokes equations and a finite volume formulation, the convective parts were discretized with the Harten TVD scheme, and the turbulence effect was modeled utilizing Menter SST two equation turbulence model. The flowfield of 18×18 degree fins generated crossing shock wave/turbulent boundary layer interactions were studied at Mach 4.96, a 3D separated flowfield was analyzed and the numerical results were compared with experimental and numerical results from references.]]></description>
<pubDate>2012/12/7 2:57:23</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[JIN Liang,LIANG Jianhan,SUN Mingbo and WANG Zhenguo]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>JIN Liang,LIANG Jianhan,SUN Mingbo and WANG Zhenguo</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200803003]]></guid><cfi:id>631</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Integrated Guidance Law of Reentry Maneuvering Warheadwith Terminal Angular Constraint]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200803005]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Because perpendicular impact on the target was required for reentry maneuvering warhead, the integrated guidance law with terminal angular constraint, which comprised diving-plane guidance equation and turning-plane guidance equation, was derived. The robustness was enhanced by adding sliding mode variable structure control to the optimal guidance law. For the sake of reduction of chattering and energy consumption, the RBF(Radius Basis Function) neural network was used to adjust adaptively switching gain, which was demonstrated to be effective through computer simulation. Simulation results still show that, compared with optimal guidance law, the integrated guidance law can still hold the guidance precision when disturbance exists.]]></description>
<pubDate>2012/12/7 2:57:23</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[HU Zhengdong,GUO Caifa and CAI Hong]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>HU Zhengdong,GUO Caifa and CAI Hong</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200803005]]></guid><cfi:id>630</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Thermodynamic Response of a Cylindrical Tunnel in the Theory ofGeneralized Thermoelastic Diffusion]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200803006]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The theory of generalized thermoelastic diffusion of Sherief is used to investigate the dynamic response of infinite elastic medium with a cylindrical tunnel subjected to a time-dependent thermal shock. Without the customary use of potential functions, the direction method of solution, with the help of Laplace technique, is used  to solve the coupling thermal, chemical and mechanical governing equation. The analytical solutions of temperature increment, displacement, stress and chemical potential are obtained in the transform domain, and by using the inverse Laplace transform, the numerical results are obtained and used to analyze the distribution of temperature increment, stress, displacement and chemical potential on the condition of thermo-chemo-mechanical coupling.]]></description>
<pubDate>2012/12/7 2:57:23</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[ZHENG Rongyue<sup>1,2</sup>,LIU Ganbin<sup>1</sup> and TANG Guojin<sup>2</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>ZHENG Rongyue<sup>1,2</sup>,LIU Ganbin<sup>1</sup> and TANG Guojin<sup>2</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200803006]]></guid><cfi:id>629</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Kelvin-Helmholtz Perturbative Wave on Hollow Conical Liquid Sheets]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200803007]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Analytical study of wave growth on hollow conical liquid sheets was made. By using small wave amplitude model, the linearized perturbation equations of the liquid phase and the gas phase were solved. After some rather tedious algebraic manipulations, the characteristic equations relating the non-dimensional temporal growth rate of a disturbance on conical liquid sheets to the normalized wave numbers were obtained. The numbers are the generalization for the well-known cases of round cylindrical jets and the annular liquid sheets. The characteristic equations are the solid cornerstone of theoretical analysis of conical liquid sheets' atomization.]]></description>
<pubDate>2012/12/7 2:57:23</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[WANG Zhongwei]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>WANG Zhongwei</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200803007]]></guid><cfi:id>628</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[A New Numerical Simulation Method for the Launch Vehicle'sStructure Transient Response in the Phases of Hold-down and Release]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200803008]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The vertical take-off event of launch vehicle was divided into static phase, hold-down phase and release phase, and the computational result fields of the previous phase provided the initial condition fields of the next phase. A new analysis method to compute the launch vehicle's structure transient response during the hold-down and release phase was proposed in this paper, using the field transferring function and group analysis function of the MSC.Patran/Nastran software. This analysis method solved the difficulty brought about by the changed boundary condition (the separate face between the launch vehicle and the launch pad) during the structure transient response computation course. Several examples of launch vehicle's structure transient response during the hold-down and release phase were analyzed by the proposed method. The variety characteristics of hold-down force during hold-down phase and the vehicle's structure transient response during the release phase were obtained. The computational results indicated that the analysis method is both simple and convenient, and the computational result was quite accurate. The method can be used to make efficient analysis of the influence of the different release time, the disappearing characteristics of the hold-down force, the dispersion of the release time, the restrain force of soft release mechanism to the vehicle's structure transient response. It can provide reference for the design of the hold-down and release mechanism.]]></description>
<pubDate>2012/12/7 2:57:23</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[WAN Jun,LI Daokui,LIU Lin and TANG Guojin]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>WAN Jun,LI Daokui,LIU Lin and TANG Guojin</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200803008]]></guid><cfi:id>627</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Research on the Fitting Algorithm of BroadcastEphemeris Parameters]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200803020]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Based on the GPS broadcast ephemeris parameters, the nonlinear least square fit algorithm of broadcast ephemeris parameters was developed, and the relevant calculation formulas were derived. Since geostationary satellite's orbit inclination is equal to zero approximately, it will result in the ambiguity of satellite's orbit ascending node and the singularity of the normal matrix in the process of fitting. By transforming the geostationary satellite's orbit inclination, the accuracy of broadcast ephemeris was achieved. Finally, the rationality of formulas and algorithm were validated by simulation.]]></description>
<pubDate>2012/12/7 2:57:24</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LIU Guangming,LIAO Ying,WEN Yuanlan and ZHU Liwei]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LIU Guangming,LIAO Ying,WEN Yuanlan and ZHU Liwei</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200803020]]></guid><cfi:id>626</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Effects of Side-inlet Angle on the Performance ofBoron-based Propellant Ducted Rocket]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200802001]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Theoretical investigation on the behavior of boron  particles in the flow field of a ducted rocket secondary combustor is presented. The study was motivated by the difficulties in achieving good combustion efficiencies of boron particles. The equation describing the gas flow field and the particle behavior were solved numerically. It is presumed that the ignition and combustion of boron particles can be controlled by King's model. The solution presents the trajectory and oxide layer thickness of the boron particles due to the interactions with the surrounding gas. Experimental investigations were done on a connected-pipe test bed. Decreasing the side-inlet angle increases combustion efficiency.]]></description>
<pubDate>2012/12/7 2:57:07</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LI Zeyong,HU Jianxin,XIA Zhixun and WANG Zhenguo]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LI Zeyong,HU Jianxin,XIA Zhixun and WANG Zhenguo</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200802001]]></guid><cfi:id>625</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Analysis on Kinematical Constraint Characters of the LaunchWindow and the Fast Design Method for Trans-lunar TrajectoryBased on the High Elliptical Parking Orbit]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200802002]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Through the analysis on kinematical constraint characters of the launch window for Earth-to-Moon transfer trajectories based on the high elliptical parking orbit, laws of kinematical constraint influence on the launch window are given, and launch opportunities of the lunar probe and the probability to add the launch window are verified. According to the kinematical constraint characters of the launch window, a fast design method for the Earth-to-Moon transfer trajectory based on the high elliptical parking orbit is provided. The simulation results show that the analysis on kinematical constraint characters of the launch window for Earth-to-Moon transfer trajectories based on the high elliptical parking orbit is correct and the design method for transfer trajectory is effective.]]></description>
<pubDate>2012/12/7 2:57:07</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[XI Xiaoning and GAO Yudong]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>XI Xiaoning and GAO Yudong</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200802002]]></guid><cfi:id>624</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Fault Simulation of Space Power System in the Operation Process]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200802003]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The dynamic characteristics in the abnormal operation process of the gelled propellant space power system is dealt with in this paper. For the purpose of setting up the fault patterns of the space power system, the fault property equations and the normal mathematical models in the operation process were built. Then, four faults, including pipeline leak, filter jam, valve fault and nozzle ablation, were simulated by the visual C++ software. With an analysis of the results, some foundation for the intelligent fault diagnosis of the space power system in the future is provided.]]></description>
<pubDate>2012/12/7 2:57:07</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[FAN Zhongze<sup>1</sup> and HUANG Minchao<sup>2</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>FAN Zhongze<sup>1</sup> and HUANG Minchao<sup>2</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200802003]]></guid><cfi:id>623</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Space RVD Terminal Approach to Attitude Tracking byTerminal Sliding Mode Control]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200802004]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[For the attitude control problem of terminal approach phase of RVD, the feedback linear theory was adopted to linearize nonlinear attitude dynamics, and a phase-variable states space model was deduced. The terminal sliding mode control theory considering the disturbances was used on the basis of the deduced model. Furthermore, this paper introduces a controller which implements the attitude tracking and controls the states tracking errors convergent to zero in the finite time. For the example given, the control results satisfy the terminal time constrain and the tracking errors were convergent to zero, and this demonstrates that the controller is robust.]]></description>
<pubDate>2012/12/7 2:57:07</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LIU Luhua<sup>1</sup>,TANG Guojian<sup>1</sup> and YU Menglun<sup>2</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LIU Luhua<sup>1</sup>,TANG Guojian<sup>1</sup> and YU Menglun<sup>2</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200802004]]></guid><cfi:id>622</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Effects of Different Silica Sol Doping Methods on the Propertiesof Fluoro-acrylate Polymer/SiO<sub>2</sub> Hybrid Coatings]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200802005]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Silica sols were synthesized by an acid-catalyzed  sol-gel process and fluoro-acrylate polymer/SiO<sub>2</sub> hybrid materials were prepared by the in-situ polymerization and blending method. The structure, morphologies of the hybrid coating and the dispersion of SiO<sub>2</sub> in coatings were characterized by FT-IR and SEM. The effects of content, distribution and interfacial conditions of inorganic disperse phase on the surface and mechanical properties of hybrid coatings were investigated. It was found that in the hybrid coatings, SiO<sub>2</sub> subsisted in networks, and covalent linked with organic components. The dispersion of SiO<sub>2</sub> in coats prepared by in-situ polymerization method was better than that by blending method. The water contact angles were enhanced with SiO<sub>2</sub> content for the coatings by the two methods, while in the same SiO<sub>2</sub>content, the properties for the coatings by blending method were slightly better than  that by in-situ polymerization method. The hardness and adhesion of the hybrid coatings had the same trend with the increase of SiO<sub>2</sub>content, in-situ polymerization method was better than that by blending method.]]></description>
<pubDate>2012/12/7 2:57:07</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[QIAN Siwen,WANG Jianfang,WU Wenjian and LIU Changli]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>QIAN Siwen,WANG Jianfang,WU Wenjian and LIU Changli</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200802005]]></guid><cfi:id>621</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Spin Attitude Measure Based on Stereo Vision]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200802022]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[To measure the aircraft model attitude in the spin time, a method based on stereo vision is presented. We get the attitudes from a set of man-made signs on the surface of the model. From a pair of figures of the signs, their disparities are computed out. The design of the signs and the computation of the attitudes are presented in this paper. The man-made signs have good identifiability and the anchor points are accurate. Finally, the data of experiments to determine the aircraft model attitude are provided. Through the experiments, it can be concluded that the process of the computing is satisfactory, achieving high robustness. The measurement shows that the method discussed is useful for the experiments in the vertical wind tunnel.]]></description>
<pubDate>2012/12/7 2:57:08</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LI Pei,LUO Wusheng and LI Guanzhang]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LI Pei,LUO Wusheng and LI Guanzhang</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200802022]]></guid><cfi:id>620</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Methods of Measuring and Evaluating the Fragments'Speed in Missile Flight Tests and Their Error-model]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200802025]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The measure of fragment's speed is a difficult problem in missile damaging-flight tests, and exact measure results are very important for the evaluation of weapon's damage effect and other technical parameters. Based on domestic actuality, the basic principles of the measure and evaluation methods of missile fragment's speed are summarized. The error sources of measure and evaluation of fragment's speed are discussed in each method discussed in the research. In view of the characteristics of the missile damaging-flight tests and the actual instance of the range, the error and error sources of single fragment's speed under the method of Reticulate Targets Method are analyzed. The corrected error model and the technique of improving speed measure's precision are put forward. The flaw and improving direction of the scheme normally used are pointed out. The results of the research have partially applied to the missile damaging-flight tests.]]></description>
<pubDate>2012/12/7 2:57:08</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[FU Changhai<sup>1,2</sup>,HUANG Kedi<sup>1</sup>,ZHANG Fenglin<sup>2</sup> and TAN Feng<sup>2</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>FU Changhai<sup>1,2</sup>,HUANG Kedi<sup>1</sup>,ZHANG Fenglin<sup>2</sup> and TAN Feng<sup>2</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200802025]]></guid><cfi:id>619</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Experimental Investigation on the Start Performancesof the Supersonic Annular Air Ejector]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200801001]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The air ejector test facility was established to investigate the start performance of supersonic annular ejector. The investigation indicates that the higher the mach number in pipe, the higher start pressure and vacuum in cavity, and that the mixing room contraction ratio and the pipe configuration of the system deeply influence the start performance, but they have little influence on the vacuum in cavity.]]></description>
<pubDate>2012/12/7 2:56:53</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[ZOU Jianjun,ZHOU Jin,XU Wanwu and WANG Zhenguo]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>ZOU Jianjun,ZHOU Jin,XU Wanwu and WANG Zhenguo</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200801001]]></guid><cfi:id>618</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Dynamic Analysis of Constrained Layer Damping Plate by theTransfer Function Method]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200801002]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The dynamic problem of constrained layer damping (CLD) plate was investigated with the transfer function method in this paper. The equations of motion and the boundary conditions were derived by using the Hamilton principle. Then the unknown displacements were expressed in Fourier series. With the introduction of the state vector, the governing equation in state space was established by the distributed parameter transfer function method. The closed-form solutions of natural frequencies, loss factors and curves of frequency response of a simply supported CLD plate were obtained. Numerical predictions of this paper agreed very well with the results of NASTRAN.]]></description>
<pubDate>2012/12/7 2:56:53</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LI Enqi,TANG Guojin,LEI Yongjun and LI Daokui]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LI Enqi,TANG Guojin,LEI Yongjun and LI Daokui</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200801002]]></guid><cfi:id>617</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[The Analyze of the Launch Window for Space Rescue Mission]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200801003]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Based on the characteristics of launch window, an algorithm to calculate the launch window for space rescue mission was deduced. The problem of the launch window was divided into the plane window problem and the phase window problem. Analytical models of the two problems were established, and the analytical result of launch window was obtained. The launch windows of launch points with different latitudes in the same longitude were described with visualization curves, which served as the basis to calculate and analyze the launch window for space rescue mission.]]></description>
<pubDate>2012/12/7 2:56:53</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LI Jiuren,LI Haiyang and JIANG Zicheng]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LI Jiuren,LI Haiyang and JIANG Zicheng</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200801003]]></guid><cfi:id>616</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[The Prediction of the Service Life of Solid MotorGrain with Cohesive Cavities]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200801004]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Cohesive cavities often occur in the solid missile motor grain. The strain field analysis of the cohesive cavity is an important problem to the evaluation of grain structural integrity. In this paper, a method to analyze the cohesive cavity's strain field is presented. With accelerated aging test, the variation law of the extensibility of propellant in the storage period was obtained. Using three-dimension viscoelastic finite element method, the Von Mises strain of the grain with cohesive cavities under internal pressure and axial acceleration loading was analyzed. In comparing the extensibility of propellant and the Von Mises strain of the grain in different storage period, the allowable maximum diameter of the cohesive cavity in different storage period was determined by the maximum Von Mises strain criterion. The analysis of a practical motor shows that the analytical method and these conclusions are available for using solid motor with cohesive cavities.]]></description>
<pubDate>2012/12/7 0:00:00</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LI Jiutian<sup>1</sup>,LEI Yongjun<sup>1</sup>,YUAN Duancai<sup>1</sup>,SHEN Zhibin<sup>1</sup> and MENG Shangyang<sup>2</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LI Jiutian<sup>1</sup>,LEI Yongjun<sup>1</sup>,YUAN Duancai<sup>1</sup>,SHEN Zhibin<sup>1</sup> and MENG Shangyang<sup>2</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200801004]]></guid><cfi:id>615</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Landing Position and Attitude Measurementof UAV Using Runway Image]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200801005]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[A new method of landing position and attitude measurement of UAV using only one runway image, which is proved applicable to such circumstance as UAV approaching to the ground while the runway width is known, is proposed in this paper. Firstly, the relation between the attitude and the vanishing point of runway was analyzed. Then, the collinearity equation was transformed by the runway line and the image line equations coefficients. Furthermore, the position along runway and the bank angle was simplified on the basis of the reasonable assumption. In so doing, the landing position and attitude of UAV was calculated by previous relations. Simulate experiment results show that the new way is easy to realize and can satisfy the application requirement of autonomous landing.]]></description>
<pubDate>2012/12/7 2:56:53</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[ZHANG Xiaomiao,SHANG Yang,LEI Zhihui and YU Qifeng]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>ZHANG Xiaomiao,SHANG Yang,LEI Zhihui and YU Qifeng</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200801005]]></guid><cfi:id>614</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Estimation Positioning Accuracy of Satellite Navigation System]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200801006]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The estimation of system accuracy is an important part in designing the satellite navigation system and a major indicator in assigning the large-scale system as well. Thus, much attention should be paid to simulating, computing and analyzing characteristics of all the error sources and their influences on system accuracy in designing satellite navigation system. This paper induces the covariance estimating expression of system positioning accuracy by differentiating the measure equations and the set of theory and method for controlling the critical error sources, which apply to engineering, is provided.]]></description>
<pubDate>2012/12/7 2:56:53</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[WANG Li]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>WANG Li</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200801006]]></guid><cfi:id>613</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Experimental Investigation on Ignition of H<sub>2</sub>O<sub>2</sub>/HTPBHybrid Rocket Engine]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200801007]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[An innovative igniter based on catalytic decomposition of H<sub>2</sub>O<sub>2</sub> was designed and manufcatured. With this igniter, an H<sub>2</sub>O<sub>2</sub>/HTPB hybrid rocket engine was tested. The experiment results demonstrate that this new igniter can successfully start the H<sub>2</sub>O<sub>2</sub>/HTPB hybrid rocket engine with 　combustion stability and good performance. The experiment results also show that the combustion efficiency will achieve the highest level when the hybrid ratio deviates from the best ratio of oxidizer.]]></description>
<pubDate>2012/12/7 2:56:53</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[SONG Zhibing,WANG Zhenguo,ZHANG Wei,XIA Zhixun and HU Jianxin]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>SONG Zhibing,WANG Zhenguo,ZHANG Wei,XIA Zhixun and HU Jianxin</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200801007]]></guid><cfi:id>612</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Numerical Simulation of Magnetohydrodynamic (MHD) Control on2D Diffuser's Flow Field]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200906008]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Conventional diffuser is introduced briefly and its mechanism is analyzed. Full Navier-Stokes equations based on low magnetic Reynolds number assumption with Favre weighted average mass are used to simulate the flow field in supersonic diffuser with added electric and magnetic field. Compared with conventional diffuser, it is obvious to see that the deceleration and expansion are realized in shorter distance when proper electric and magnetic field added, and part of the kinetic energy is transformed into electric energy. Study shows that the positions of the first shock wave, and the second shock wave and the length of shock train in the diffuser when certain magnetic field added are respectively 62.19%, 77.74% and 50.18% to the ones of conventional diffuser.]]></description>
<pubDate>2012/11/8 3:50:44</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[ZHANG Kangping,DING Guohao,TIAN Zhengyu and LI Hua]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>ZHANG Kangping,DING Guohao,TIAN Zhengyu and LI Hua</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200906008]]></guid><cfi:id>611</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[6-DOF Synchronization Control Approach Strategy for SpaceRobots Capture Mission]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200906009]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[On-orbit capture by space robots is one of the main modes of spacecraft on-orbit servicing. For space robots capture of uncontrolled rotating satellites, the 6-DOF synchronization control approach strategy is investigated to improve the time horizon to suit grasp. Firstly, the target motion model is provided, and the attitude is described by modified rodrigues parameters. Then suppose that the attitude control of space robot is actuated by momentum wheels, the 6-DOF synchronization control is conducted in two phases: translational control and rotational control. In consideration of the uncertainty in inertia parameters, the control laws for translational and rotational synchronization are derived respectively by adaptive output feedback control. The simulation results show that the models and algorithms are efficient under the condition of unknown bounded disturbances and inertia parameters uncertainty.]]></description>
<pubDate>2012/11/8 3:50:44</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[ZHU Yanwei and YANG Leping]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>ZHU Yanwei and YANG Leping</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200906009]]></guid><cfi:id>610</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[The Orbital Reconfiguring Design and Analysis after ManeuverFailure for Rendezvous Phasing]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200906010]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The orbital reconfiguring problem after maneuver failure for rendezvous phasing is studied. The orbital reconfiguring design rules are proposed and four types of orbital reconfiguring plan are provided respectively for every maneuver failure in five-impulse phasing mission. Based on the proposed design rules, the provided reconfiguring plan's correcting ability, tracking and command condition, propellant consumed, terminal precision and security are analyzed. Finally, the orbital counter plan to deal with rendezvous phasing maneuver failure is obtained.]]></description>
<pubDate>2012/11/8 3:50:44</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[ZHANG Jin,LI Haiyang,LUO Yazhong and TANG Guojin]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>ZHANG Jin,LI Haiyang,LUO Yazhong and TANG Guojin</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200906010]]></guid><cfi:id>609</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[The Test and Calibration of Φ200 Hypersonic Wind Tunnel]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200906011]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The newly finished Φ200 hypersonic wind tunnel(Mach numbers 2.5 to 7) has been tested and calibrated. The results of calibration indicating total temperature, total pressure, operating time of HWT-200 have accorded with the purpose of design. HWT-200 can run within large Mach number span at supersonic/hypersonic flow. The rms of Mach numbers (σ<sub>M</sub>) at all test  sections Mach numbers from 2.5 to 7.0 reaches the requirement of GJB1179-91. A large, uniform region of flow was documented. Operational time of HWT-200 is no less than 20s. So, HWT-200 is a facility which can be used for teaching of aerodynamic experiments and elementary scientific researches.]]></description>
<pubDate>2012/11/8 3:50:44</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[ZHOU Yongwei,YI Shihe and CHENG Zhongyu]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>ZHOU Yongwei,YI Shihe and CHENG Zhongyu</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200906011]]></guid><cfi:id>608</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Optimal Design for the Feedforward-feedback Compound ControllerBased on a Hybrid Optimization Algorithm]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200906012]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Considering the fact that it is difficult for the conventional PID controller to meet control request in the aircraft control process, we designed a normalized feedforward-feedback controller system. Furthermore, the hybrid optimization algorithm that combined the chaos optimization algorithm and the conjugate gradient method was used to search for the optimum parameters of the feedforward-feedback controller system. Simulation experimental results and experimental analysis proved the superiority of the hybrid optimum feedforward-feedback controller, which showed better dynamical and steady behavior, strengthened the fitness and robustness of the system, and weakened the blindness to selection of learning factors and high dependency on experience.]]></description>
<pubDate>2012/11/8 3:50:44</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LIAO Ying<sup>1</sup>,ZHOU Baomin<sup>2</sup>,ZHONG Cheng<sup>1</sup> and CAO Denggang<sup>2</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LIAO Ying<sup>1</sup>,ZHOU Baomin<sup>2</sup>,ZHONG Cheng<sup>1</sup> and CAO Denggang<sup>2</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200906012]]></guid><cfi:id>607</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[The Maximum-range Trajectory Analysis of HypersonicGlide-reentry Vehicle]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200906013]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In order to maximize the range of reentry, the trajectory of hypersonic glide-reentry vehicle is studied. The optimal trajectory is obtained using legendre pseudospactral method (LPM). The effect of the path constraints on the trajectory is analyzed. Furthermore, the regulation of the control variable of the constrained trajectory is analyzed. According to the rule, a piecewise linear model of the coefficient of lift is proposed. Numerical simulation shows that the trajectory derived by this model is very similar to the optimal trajectory, and the ranges of the two trajectories are nearly the same, demonstrating a good control method for the maximum-range trajectory.]]></description>
<pubDate>2012/11/8 3:50:44</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[DING Hongbo,CAI Hong,ZHANG Shifeng and LI Anliang]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>DING Hongbo,CAI Hong,ZHANG Shifeng and LI Anliang</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200906013]]></guid><cfi:id>606</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Fuel-time Multiobjective Optimal Control of Flexible StructuresBased on MOEA/D]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200906014]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[A multi-objective optimization for rest-to-rest  maneuvers of flexible spacecraft is presented by using MOEA/D (Multiobjective Evolutionary Algorithm based on Decomposition). The multiobjective control design functions which deal with the minimal maneuver time and fuel consume are developed by using rigid-flexible couple dynamics model of spacecraft. A new MOEA/D approach is introduced for maneuvers problem of flexible spacecraft control system. The simulation results show that the approach can be efficiently realized in design and analysis of flexible spacecraft.]]></description>
<pubDate>2012/11/8 0:00:00</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[ZHANG Qingbin,FENG Zhiwei,LIU Zeming and YANG Tao]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>ZHANG Qingbin,FENG Zhiwei,LIU Zeming and YANG Tao</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200906014]]></guid><cfi:id>605</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Multi-objective Optimization of Reentry Trajectory for HypersonicGlide Vehicle with Multi-constraints]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200906015]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Trajectory optimization is a key technology of hypersonic glide vehicle. In order to avoid the disadvantage of indirect method's sensitivity to initial guess and pseudospectral method's difficulty to settle path constraints, a direct method based on Akima spline interpolation is proposed to solve reentry trajectory optimization problem. A numerical example that minimizes the stagnation point heat flux and fly time to target while satisfying state constraints such as vehicle dynamics, control limitation, waypoint, no-fly zone, dynamic pressure and overload is presented. Compared with literature results, the results show that the Akima interpolation can decrease the control parameter's bound violation phenomena during interpolation; the Pareto front distributed nicely, providing more choice to designer during concept design stage. Compared with the single object optimize result in literature, the algorithm adopted in this paper also shows better performance.]]></description>
<pubDate>2012/11/8 3:50:44</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[CHEN Xiaoqing,HOU Zhongxi and LIU Jianxia]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>CHEN Xiaoqing,HOU Zhongxi and LIU Jianxia</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200906015]]></guid><cfi:id>604</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Numerical Simulation of Detonation in CylindricalExplosives in Driving Tube]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200905021]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The evolution of detonation waves in cylindrical explosives in driving tube is simulated in this paper. Eulerian finite volume method is used, in which the JWL(Jones-Wilkins-Lee) state equation is used for both explosives and detonation products, while the prefect gas state equation for air, and the ignition and growth model is used to calculate chemical reaction rates. The evolution of wave structures is obtained, which can calculate detonation speed accords well with experiential formula. It is also demonstrated that the peak pressure on the side inboard of the tube is above 800MPa, and due to the converge of shock waves, the peak pressure in the center of bottom is as high as 12.4GPa.]]></description>
<pubDate>2012/11/8 3:52:02</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[BAI Xiaozheng<sup>1</sup>,LIU Ruichao<sup>2</sup> and LIU Jun<sup>1</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>BAI Xiaozheng<sup>1</sup>,LIU Ruichao<sup>2</sup> and LIU Jun<sup>1</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200905021]]></guid><cfi:id>603</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Non-linear Time Series Analysis of Evolution Status ofSupersonic Mixing Layer]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200905022]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Coherent structures of two-dimensional supersonic turbulent mixing layer with engineering background are investigated by using the method of Large Eddy Simulation (LES). Chaos characteristics of evolution status are obtained by the non-linear time series analysis of pseudo-phase portrait, Lyapunov exponent and correlation dimension. The results show that the pseudo-phase portrait of pressure can denote the stability of mixing layer. The distribution of correlation dimensions can be used to measure the evolution status of mixing layer quantificationally, and the distribution of maximal Lyapunov exponents can be used to validate the measure results above. In corresponding experiments for mixing layer, the universality of studies on evolution status of mixing layer by the method of non-linear time series analysis is testified.]]></description>
<pubDate>2012/11/8 3:52:02</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[YU Jiangfei,YAN Zhihui and LIU Weidong]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>YU Jiangfei,YAN Zhihui and LIU Weidong</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200905022]]></guid><cfi:id>602</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Collision Factor Analysis for Formation-flying Satellites]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200905023]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The factors affecting collision probabilities between formation-flying satellites are discussed and generalized, for the purpose of increasing the accuracy of the collision detection and forecast. A difference equation of Hill's equation is derived for the Kalman filter, which is used to estimate the target satellite's status. Based on these equations, such four factors as model errors, measurement errors, malfunctions and accidental events are analyzed in detail. Several simulation scenarios are also executed for the factors. The simulation results show that the controller always-functioning malfunction is the worse collision factor, which needs further researches for a specific collision avoiding scheme.]]></description>
<pubDate>2012/11/8 3:52:02</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[YANG Xuerong<sup>1</sup>,CHEN Zhonggui<sup>2</sup>,ZHAO Jiankang<sup>3</sup> and LIANG Jiahong<sup>1</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>YANG Xuerong<sup>1</sup>,CHEN Zhonggui<sup>2</sup>,ZHAO Jiankang<sup>3</sup> and LIANG Jiahong<sup>1</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200905023]]></guid><cfi:id>601</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Glideslope Guidance Algorithm for Close RangeRendezvous of Spacecraft]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200905024]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The multi-impulse glideslope guidance algorithm for close range rendezvous of spacecraft is presented. The algorithm takes the fuel economy and the constraints of field-of-view of navigation facilities, the minimum interval of impulses, and the maximum value of impulse into consideration. Furthermore, a consolidated model of glideslope algorithm to guide close range rendezvous (both proximity and departure) is described. By designing the relationship of exponential function between distance and speed of ideal rendezvous trajectory, the algorithm can be applied to any specified rendezvous time, and satisfies the need of decelerating during the proximity operation and accelerating during the departure operation. By defining the logarithmic mapping function, the optimized impulses can be obtained. Finally, several scenarios of the proximity and departure operations are simulated. In some scenarios, compared with the optimization method, the using of logarithmic mapping function can also economize fuel at a cost of low computational complexity. The other scenarios illustrate that the guidance algorithm can ensure a close range rendezvous motion in any direction, at any time with the fuel economy and under the constraints as well.]]></description>
<pubDate>2012/11/8 3:52:03</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LIANG Libo,LUO Yazhong and TANG Guojin]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LIANG Libo,LUO Yazhong and TANG Guojin</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200905024]]></guid><cfi:id>600</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Interaction Between Interleaved Installation Cavitiesin Supersonic Flow]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200904019]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Interaction between two interleaved installation cavities in supersonic flow was experimentally investigated with high speed camera and schlieren system. Results revealed that shock interaction was main affection between two cavities, shock interaction between two cavities lead to the change of cavities flowfield；double cavities with same length range(short or long) will strengthen the compression shock or expansion shock; different length cavities combine will decrease the flow strength.]]></description>
<pubDate>2012/11/8 3:52:18</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[PAN Yu,LIU Weidong and WANG Zhenguo]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>PAN Yu,LIU Weidong and WANG Zhenguo</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200904019]]></guid><cfi:id>599</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Research of Dynamics and Gear Ratio Effects on VibrationSuppression For Large Space Flexible Manipulator]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200904020]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Super-low frequency flexibility during motion is an important issue for a large space manipulator,which involves not only the bending vibration of arm exists, but also the joint torsional vibration. In joint control, what is important is to stabilize and suppress low flexible vibration of joint and arm while joint position is being controlled. How gear ratio parameters for joint structure affect vibration suppression is also a required problem to analyze in joint design of space manipulator, on which gear ratio parameters depend. Combined dynamics of flexible joint and arm for space manipulator was modeled with concentrated parameter method, one strategy of suppressing joint vibration and arm vibration simultaneously was put forward, the effect of gear ratio on vibration suppression was analyzed by numerical simulation and theoretical analysis. This will be useful in design and research of large space flexible manipulator.]]></description>
<pubDate>2012/11/8 3:52:18</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[TAN Chunlin<sup>1</sup> and LIU Xinjian<sup>2</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>TAN Chunlin<sup>1</sup> and LIU Xinjian<sup>2</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200904020]]></guid><cfi:id>598</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Combustion Performance Numerical Analysis on Two Styles ofInner Bypass for Solid Fuel Ramjet]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200904021]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Two styles of inner bypass structure, the annulus style and gear style, were numerically studied. The fuel was HTPB while the overall reaction process and Eddy-Dissipation Model were adapted. It was concluded that the combustion in the dump afterburning chamber of annulus style was still controlled by diffuse. The gear style could induce couples of symmetrical vortexs in the head of dump afterburning chamber, which could enhance the mixing effect of unburned fuel and bypass air, and the total pressure loss was approximately  approaching the annulus style, thus the combustion performance of gear style performs better.]]></description>
<pubDate>2012/11/8 3:52:18</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LIU Wei,YANG Tao,CHENG Xinghua and LI Li]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LIU Wei,YANG Tao,CHENG Xinghua and LI Li</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200904021]]></guid><cfi:id>597</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Study on Formation Keeping for Coplanar Flying-aroundSatellites Based on Combined Maneuver]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200904022]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The figure of the relative kinematical track of the coplanar flying-around satellites is an ellipse. However, the configuration of the formation flying will change because of the disturbing force. A new formation keeping strategy based on combined maneuver was developed. In Hill orbital coordinates, through the measurement of the relative position components of the flying-around satellites, the combined control of the tangential impulse thrust and the constant continuous radial thrust eliminated the phase excursion of the center of the relative kinematical ellipse. Then the method considering the J<sub>2</sub>perturbations was applied to improve the control accuracy. Simulation results show that this control strategy has nice performance on formation keeping.]]></description>
<pubDate>2012/11/8 3:52:18</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LIU Guangming<sup>1</sup>,WEN Yuanlan<sup>1</sup>,YANG Xuerong<sup>2</sup> and LIAO Ying<sup>1</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LIU Guangming<sup>1</sup>,WEN Yuanlan<sup>1</sup>,YANG Xuerong<sup>2</sup> and LIAO Ying<sup>1</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200904022]]></guid><cfi:id>596</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Numerical and Experiment Studies on Water Ramjet withEffect of Water-fuel Ratio]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200904023]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[A two-phase reaction model of the secondary combustor was established to study the effect of water-fuel ratio on engine performance of magnesium-based water ramjet with twice water penetration. The change tendency of specific impulse, temperature and velocity of nozzle exit were obtained with water-fuel ratio. Direct-connected tests were carried out in order to validate the correctness of the numerical simulation. The result shows that there exists the optimum water-fuel ratio, which can improve the performance of water ramjet.]]></description>
<pubDate>2012/11/8 3:52:18</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[HAN Chao,XIA Zhixun,HU Jianxin,ZHAO Ning and FANG Dingyou]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>HAN Chao,XIA Zhixun,HU Jianxin,ZHAO Ning and FANG Dingyou</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200904023]]></guid><cfi:id>595</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Parallel One-dimensional Model for Transient ThermalAnalysis of Metallic Thermal Protection System]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200904025]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[A parallel one-dimensional model for transient thermal analysis of the metallic thermal protection system (MTPS) for reusable launch vehicle (RLV) is established. Firstly, several heat roads are defined according the structure of the MTPS. The implicit differential formulation of single heat road is given after the discretization of heat roads. Then, the local control equations for series-wound and parallel public nodes are given with the heat equilibrium method. Furthermore, the uniform formulas of the usual boundary conditions are presented. Finally, the global control equation is gained. The transient temperature field is obtained with numerical calculation. The results show that the heat transfer process can be predicted more credibly and accurately by the adoption of the parallel one-dimensional model, which can also provide a more valuable reference for the optimization design of MTPS.]]></description>
<pubDate>2012/11/8 3:52:18</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LI Daokui,DUAN Jingbo and LEI Yongjun]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LI Daokui,DUAN Jingbo and LEI Yongjun</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200904025]]></guid><cfi:id>594</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Research on the Supersonic Two Phase Flow Liquefaction Equipment]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200903001]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Liquefaction scheme based on the supersonic lifting-pressure principle of steam injector has good performance on outlet pressure and liquefaction speed. However, the physical proceed of equipment is very complex; many parameters haven't been contained in the theory equations. The paper established the theory equations which consider the heat and mass transfer between the steam and water. The effects made by the coolant water temperature, injection coefficient, convergent ratio, water undercooling and speed difference are analyzed. The results show that the water should be atomized as smaller as possible, the coolant temperature should be lower, and injection coefficient should be 6～8. If design is correct, the lifting-pressure ratio of the convergent-divergent type steam injector can reach three times than the original.]]></description>
<pubDate>2012/11/8 3:52:31</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[HUANG Yiyong and XU Junxiao]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>HUANG Yiyong and XU Junxiao</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200903001]]></guid><cfi:id>593</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Two-way Coupled Model for Rarefied Multiphase Flow]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200903002]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Based on the DSMC method, a two-way coupled mechanical and thermal model for high-altitude two-phase rarefied flow is presented with considering of particles' micro flow properties. An approach of DSMC is developed for multiphase flow in the transitional regime of rarefied gas. Simulations are performed for the verified case and the results show that the model agrees closely with the momentum and energy transfer mechanism.]]></description>
<pubDate>2012/11/8 3:52:31</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LI Jie,YIN Le and YAN Li]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LI Jie,YIN Le and YAN Li</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200903002]]></guid><cfi:id>592</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Analysis of Parachute's Deployment Load and InfluentFactors Based on Orthogonal Experiment Method]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200903003]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Influent factors' sensitivity in the huge parachute's deployment load is discussed in this paper. The dynamic model during parachute inflation is based on the inflation time method, the numerical experimentation is designed by orthogonal experiment approach for analyzing the influence and sensitivity of 21 parameters such as initial conditions, recovery object parameters, pilot parameters, main parachute parameters and environment conditions etc. about 5 indexes such as two parachutes' deployment force peak and the dynamic pressure when the main parachute deployed. Four numerical experiment results obtained from four different initial conditions are compared in this paper, the main factors which influence pilot and main parachute's deployment load are presented, and the influent mode of every factor is concretely analyzed.]]></description>
<pubDate>2012/11/8 3:52:31</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[DING Di and QIN Zizeng]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>DING Di and QIN Zizeng</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200903003]]></guid><cfi:id>591</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Dynamic Model and Simulation of Orbital NetCasting and Ground Test]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200903004]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Orbital net capture is an innovative mission concept, and has special potential on space debris disposal and OOS (on-orbit service). Dynamics of orbital net casting is a key technique of the orbital net capture system design and application, for which two major feasible investigation means have been suggested: dynamic modeling, simulation and ground test. Based on dumped-mass model, a model of the system dynamics was derived, and a ground test device was designed to verify the simulation result. The comparison of several ground tests and simulations shows that the model can be used to design orbital net capture systems. Relevant pictures of ground test and simulation were presented.]]></description>
<pubDate>2012/11/8 3:52:31</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[CHEN Qing,YANG Leping and ZHANG Qingbin]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>CHEN Qing,YANG Leping and ZHANG Qingbin</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200903004]]></guid><cfi:id>590</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[The Aging Property and Life Prediction of NEPEPropellant under Constant Strain]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200903005]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The thermal aging properties, including the mechanical property, the gel property and interfacial property, were measured to analyze the aging characteristics of nitrate ester plasticized polyether (NEPE) propellant during aging process under 20% constant strain. The results show that the maximum tensile strength is decreased while the elongation at maximal has no obvious change. The performances deterioration of NEPE propellant is the invalidation of the strength. The gel fraction and the work of adhesion are decreased along with the aging time. The main aging mechanism is the degradation of the binder matrix and interfacial dewetting. There is a correlation between the maximum tensile strength and the gel fraction, the adhesion work. The equation is calculated to determine the relationship. The method is established to evaluate the macroscopical mechanical property by microcosmic property. Storage life of propellant under 20% constant strain is 8.3 years, while the value of deterioration of maximum tensile strength changes to 30%, it will reach the invalidation point.]]></description>
<pubDate>2012/11/8 3:52:31</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[ZHANG Xinggao,ZHANG Wei,WANG Chunhua and ZHU Hui]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>ZHANG Xinggao,ZHANG Wei,WANG Chunhua and ZHU Hui</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200903005]]></guid><cfi:id>589</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[An Approach of Accurate Impulse Transfer Based onLambert Algorithm]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200903007]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The solutions to Lambert problem are mostly based on two-body supposition, which may bring inconvenience to accurately control of orbital transfer. Therefore, an approach to amend the impulses of Lambert transfer is presented. In terms of the perturbation, the precise dynamical model of spacecraft is established. Based on the result of Lambert algorithm, Quasi-Newton iterative method is employed to correct the impulses and reduce the errors of final state in orbital transfer. The approach is then used in the problem of time-fixed accurate impulse transfer. Finally, a two hierarchical programming model is established to solve the problem, which was proved to be right by an example.]]></description>
<pubDate>2012/11/8 3:52:32</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[SANG Yan and ZHOU Jin]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>SANG Yan and ZHOU Jin</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200903007]]></guid><cfi:id>588</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Derivation of Linearization Small Deviation Equations and Designof Compound Control System for Aid-sliding Vehicles]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200903009]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The aid-sliding technology is the one of key technologies for guided weapons to augment the range and enhance maneuver penetration ability. This technology has a high demand on vehicle's attitude control and the compound control system. Aiming at vehicles controlled by the linkage mode with aerodynamic rudders and gas rudders, the integrated dynamic model is set up and the complete linearization small deviation equations on pitching, yawing and roll loops are elaborated in the derivation. Combined with typical trajectory data, figures of dynamic coefficients are presented, and according to these figures, the vehicle's stability in each phase of the boost gliding trajectory is analyzed. On the basis of the above work, the low altitude point 260s in reentry phase is picked as characteristic point and the attitude control system of this point is designed. Simulation results indicate the correctness of linearization small deviation equations and the validity of the control system. This research can provide helpful reference to stability analysis and designing attitude control system for this kind of vehicles.]]></description>
<pubDate>2012/11/8 3:52:32</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[ZHAI Hua<sup>1</sup>,GU Zhijun<sup>1</sup>,LIU Juan<sup>2</sup> and ZHOU Bozhao<sup>1</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>ZHAI Hua<sup>1</sup>,GU Zhijun<sup>1</sup>,LIU Juan<sup>2</sup> and ZHOU Bozhao<sup>1</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200903009]]></guid><cfi:id>587</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[High Precision Real-time Simulation of GPS Measurement]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200903013]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[This paper presents a real-time system structure for high precision GPS measurement simulation. Firstly, the principle, function composing and appropriate mathematical models used in measurement simulation were studied. Secondly, according to different time constrains of different models' realization, a distributed simulation system was proposed to simulate GPS measurement. The system was divided into negative real time part, week real time part  and strong real time part accordingly. Finally, an investigation experiment was made. The results showed that simulation system could satisfy the strong real time demand, and the simulated measurement reached a good degree of accuracy.]]></description>
<pubDate>2012/11/8 3:52:32</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[FAN Guoqing,WANG Wei and XI Xiaoning]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>FAN Guoqing,WANG Wei and XI Xiaoning</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200903013]]></guid><cfi:id>586</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Research of the Vibration Failure of the Large Flux PRV]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200902001]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The pressure vibration failure of the large flux pressure reducing valve (PRV) was analyzed. A dynamic mathematical model of the PRV system was developed to simulate this failure, and a simple and effective method of reducing the area of the control cavity inlet to enhance the stability of the pressure output response of the PRV was found by the simulation and validated by the experiments. The result of the simulation shows that the vibration problems of the large flux PRV are related not only to the design parameters of the PRV, but also to the backward tubes connecting to the PRV.]]></description>
<pubDate>2013/1/31 4:04:32</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LAI Lin,LI Qinglian,ZHENG Li and ZHOU Jin]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LAI Lin,LI Qinglian,ZHENG Li and ZHOU Jin</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200902001]]></guid><cfi:id>585</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[The Influence of Dual-cavity on Pilot HydrogenDistribution in Scramjet Combustor]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200902002]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In order to investigate the influence of multi-cavity on gas fuel distribution in scramjet combustor, the numerical simulation was used to analyze the pilot hydrogen jet, which was used to pilot kerosene into cold flow in scramjet. The analysis was conducted in three aspects: firstly, dual-cavity combustor with cavities in tandem was compared with single-cavity combustor, with the result showing that the center of hydrogen jet leans to the main stream because of the downstream cavity. Secondly, in dual-cavity combustor with cavities in tandem, upstream cavity was compared with downstream cavity in fuel distribution. The result reveals that hydrogen spreads more extensively in the Z axis direction in upstream cavity, while it spreads wider in Y axis direction in downstream cavity. Finally, the dual-cavity combustor with cavities in parallel was compared with single-cavity combustor. The result indicates that cavity which is in the bottom wall has no influence on gas fuel distribution.]]></description>
<pubDate>2013/1/31 4:04:32</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LIU Juan,PAN Yu,LIU Weidong and WANG Zhenguo]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LIU Juan,PAN Yu,LIU Weidong and WANG Zhenguo</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200902002]]></guid><cfi:id>584</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Several Relative Formation of Spacecrafts Flight in HighlyElliptic Orbits Based on Relative Orbit Elements]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200902003]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The spacecraft on highly elliptic orbit flies over their apogee in the most part of one period. So this kind of orbit can be used to realize long term communication and airborne early warning for high latitude areas, which is significant if applied in military. The kinematics of multi-spacecraft formation is required to deal with space missions such as the exploration of space magnetic fields and the information interference. Formulations of the relative motion on highly elliptic orbits are developed by kinematic method which takes the relative orbit elements as the variable, and then the precision of the formation is analyzed. Based on the formation, several special relative formations including the linear circular elliptical and isosceles triangle ones are discovered, and the conditions to form these formations are presented. Under the circumstance of two-body, the results from simulation show that the more close of the spacecrafts, the more accurate of the formations.]]></description>
<pubDate>2013/1/31 4:04:32</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[WANG Gongbo and XI Xiaoning]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>WANG Gongbo and XI Xiaoning</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200902003]]></guid><cfi:id>583</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[The Integrated Autonomous Orbit Determination of the NavigationConstellation Based on Crosslink Range and Ground-based Emitter]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200902004]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The autonomous orbit determination of navigation constellation is one of the key techniques of the Compass Navigation Satellite System (CNSS). There, howerver， is a deficiency problem of the datum mark when only intersatelite measurements of range is used. To solve this problem, this paper presents a new method that a few ground-based radio emitters should work randomly to offer the benchmark, and the constellation satellites should estimate their position and velocity for the whole network, based on the fusion of crosslink pseudo-range measurements and ground-based measurements. It is aimed to improve the orbit determination accuracy ulteriorly. Finally, the simulation results prove the rationality and validity of this method.]]></description>
<pubDate>2013/1/31 4:04:32</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[ZHU Jun,LIAO Ying and WEN Yuanlan]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>ZHU Jun,LIAO Ying and WEN Yuanlan</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200902004]]></guid><cfi:id>582</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[A Method to Extract the Runway for Airborne VisionBased  Auto-landing]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200902005]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Extracting the linear parameters of the runway is the precondition for airborne vision based auto-landing. Firstly it is required  to obtain a lot of short lines by gradient direction grouping on the edge map. Secondly according to the angle between two lines and the distance between the ends of two lines, and the gray average on both sides of lines, a rule to quantitatively characterize the affinity between two short lines is advanced, then the short lines on the same line end-to-end by the value of affinity will be linked. Finally the longest lines are left to choose, and priori knowledge, namely the contrast information of shades between the internal and external runway is applied to distinguish the two lines lying on the two edges of the same runway. The method has been tested valid by many actual images.]]></description>
<pubDate>2013/1/31 4:04:32</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[ZHU Xianwei,LI You and YU Qifeng]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>ZHU Xianwei,LI You and YU Qifeng</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200902005]]></guid><cfi:id>581</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Trans-lunar Trajectory Design of Lunar Probe Launchedfrom Space Station]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200902006]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Because of the fixed orbit of the space station in inertia space, it is important to design the trans-lunar trajectory of the probe based on the space station assembly. In this paper, considering the kinematic law of the moon, an integrated mathematical model for trans-lunar trajectory design is established, and the constraint conditions are presented according to practical situations in engineering. Then the main problem for orbit design is to solve the orbit dynamics equation in some constraint conditions. Appropriate object function and constraint conditions are chosen, and the equation is solved by using genetic algorithm and SQP method. The parameters of trans-lunar trajectory are calculated by using numerical method. Finally, by a comparison with the data gained from STK, the results are validated.]]></description>
<pubDate>2013/1/31 4:04:32</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[PENG Qibo,LI Haiyang,LI Zhen and TANG Guojin]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>PENG Qibo,LI Haiyang,LI Zhen and TANG Guojin</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200902006]]></guid><cfi:id>580</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Numerical Simulation for Shock Induced InterfacialInstabilities of Heterogeneous Gases]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200901001]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Based on the 2-D Navier-Stokes equations, the shock induced interfacial instabilities of heterogeneous gases was simulated numerically With the finite differential method. After carrying out the comparison between numerical and experimental results, the unsteady and nonlinear characteristics of the flow field was analyzed. From the results, it is observed that the unsteady flow field of numerical simulation is similar to referenced experimentation and CFD results, and the evolvement of sulphur hexafluoride interface and the complicated wave structures are captured from simulation.]]></description>
<pubDate>2012/11/8 3:52:57</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[ZHOU Songbai,LIU Jun,GUO Zheng and LIU Yu]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>ZHOU Songbai,LIU Jun,GUO Zheng and LIU Yu</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200901001]]></guid><cfi:id>579</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Analysis of the Scattering Characteristic for the HypersonicFlow Field with Near Wake Region of Sphere]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200901002]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[A piecewise linear JE recursive convolution finite-difference time-domain (PLJERC-FDTD) algorithm is applied to the study of the scattering characteristics of the hypersonic flow field with near wake region of conductive metal sphere. The effects of incidence wave frequency, incidence angle, scattering angle, polarization angle, altitude and Mach number on the radar cross section (RCS) are analyzed. The results illustrate that the forward RCS is the maximal RCS of all scattering orientations' RCS. The forward RCS increases with the rise of incidence wave frequency and Mach number, decreases with the decline of altitude when the Mach number is not less than 14 in this article. The backward RCS and the bistatic RCS of flow fields vary very small with Mach number, altitude and incidence angle for UHF, L and S band, the margin of the backward RCS between flow fields and sphere are small when the Mach number is not more than 10. The backward RCS of flow fields is more than the sphere's because of the formation of wide over-dense plasma wake, the curve of backward RCS varies when the incidence wave frequency can be approached by one line for L, S band if the incidence orientation is perpendicular to the X-axis and the Mach number is not less than 14.]]></description>
<pubDate>2012/11/8 3:52:57</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[CHANG Yu<sup>1</sup>,CHEN Weifang<sup>2</sup> and WU Qifen<sup>1</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>CHANG Yu<sup>1</sup>,CHEN Weifang<sup>2</sup> and WU Qifen<sup>1</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200901002]]></guid><cfi:id>578</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[An Initial Orbit Determination Method Using Space-based Angle Data]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200901003]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[A space-based orbit determination method using angle data is discussed in this article, which proposes the method of Vector Projection by unifing several present methods. It is convenient to be extended for other data types, and to build the based condition equations. Meanwhile, the correlative issues are studied, such as evaluation of initial iteration values, elimination of uniform solution and iteration acceleration. The numerical simulations in the end show that the new method is effective and swift in achieving a satisfying result.]]></description>
<pubDate>2012/11/8 0:00:00</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LIU Lei,XI Xiaoning and CHEN Haiping]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LIU Lei,XI Xiaoning and CHEN Haiping</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200901003]]></guid><cfi:id>577</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Investigation on Lunar Mission Based on Lunar Orbit Rendezvous]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200901004]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[A schematic manned lunar mission case based on coplanar lunar orbit rendezvous is investigated. Based on the principle of splitting the crew and cargo, the flight case including 3 launches and 2 rendezvous is designed. The launch window meeting the restriction of coplanar rendezvous and the characteristics of trans-lunar trajectory is obtained by precise dynamics model. Finally, the 3 missions of flight are arranged and the scale is estimated. The result from simulation shows that the TOF(time of flight) and energy of this mission case are feasible.]]></description>
<pubDate>2012/11/8 3:52:57</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LI Zhen,ZHOU Jianping,CHENG Wenke,LI Haiyang and PENG Qibo]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LI Zhen,ZHOU Jianping,CHENG Wenke,LI Haiyang and PENG Qibo</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200901004]]></guid><cfi:id>576</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Parameters Analysis of Ignition Transient in SolidRocket Motor with Rear Igniter]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200901005]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[With a quasi 1-D unsteady flow model, a numerical simulation is completed to analyze the ignition transient in a small solid rocket motor activated by a rear igniter. Based on the simulation results, a detailed parameter analysis is performed for some key factors which may heavily affect the performance of ignition transient. The results can provide a useful guide for the matching design between the rear igniter and the nozzle seal.]]></description>
<pubDate>2012/11/8 3:52:57</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[FAN Chao and ZHANG Weihua]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>FAN Chao and ZHANG Weihua</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200901005]]></guid><cfi:id>575</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Research on Multidisciplinary Design Optimization of Tactical Missile]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200901006]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The multidisciplinary system analysis models for tactical missile are derived, and the multidisciplinary design optimization (MDO) methods are established accordingly. MDO methods can gain the optimal design consistent with system design constraints and the solid rocket motor thrust time curve, which is a best match for exterior trajectory by looping execution between system design optimization and parallel subsystem solid rocket motor design optimization, thus the design cycle for tactical missile system and solid rocket motor can be greatly reduced. The tactic-technical specifications, including the motion state of 22 typical targets, are taken into account in the design optimization process of tactical missile.]]></description>
<pubDate>2012/11/8 3:52:57</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[ZOU Ruping<sup>1</sup>,LI Xiaobin<sup>1,2</sup> and ZHANG Weihua<sup>1</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>ZOU Ruping<sup>1</sup>,LI Xiaobin<sup>1,2</sup> and ZHANG Weihua<sup>1</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/200901006]]></guid><cfi:id>574</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[An Overview of the Researches on Whipcrack Phenomenon]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201006012]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[After presenting the experimental and theoretical researches on whipcrack phenomenon, the current study gives a particular description of Krehl's experimental results, the whip models based on conservation of energy and based on conservation of momentum, and the current researches on this unique phenomenon. Finally, the characteristics of whipcrack were acquired, and the comparison between the whipcrack and other large flexible structures ‘swing  phenomena such as the huge parachutes’ whip or the “probe-drogue” in-flight refueling system's whip showed that there was much comparability, so the study of the whipcrack phenomenon will help researchers obtain a better understanding of these phenomena.]]></description>
<pubDate>2012/8/28 16:33:32</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[QIN Zizeng<sup>1</sup>,GUO Peng<sup>1</sup>,TAO Wusha<sup>2</sup> and XIA Gang<sup>1</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>QIN Zizeng<sup>1</sup>,GUO Peng<sup>1</sup>,TAO Wusha<sup>2</sup> and XIA Gang<sup>1</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201006012]]></guid><cfi:id>573</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[A New Method of Guidance for Proximity ScanningInspection of Non-cooperative Space Target]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201006013]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[With the development and application of micro-satellites, proximity inspection of spacecraft has become a new area of space mission. It plays an important role in Space Situational Awareness and on-orbit servicing, ensuring broad application prospects. The current study developed a new method of guidance for proximity scanning inspection of non-cooperative space targets based on the modified artificial potential field method. First, the attractive potential function and repulsion potential function were formulated. The former, parallel to the surface of the target, guides the inspector from the initial position to the goal position. The latter, perpendicular to the surface of the target, is used to deal with the constraint conditions like image resolution, minimum angle of observation and collision avoidance constraint etc. Simulation results demonstrate that the inspector can follow the surface of the target well and conduct a coherent and stable scanning inspection. Furthermore, it requires less computational effort and is easier to realize on the inspector.]]></description>
<pubDate>2012/8/28 16:33:32</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[REN Xianhai,YANG Leping and ZHU Yanwei]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>REN Xianhai,YANG Leping and ZHU Yanwei</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201006013]]></guid><cfi:id>572</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Investigation on a WENO Scheme Based on Low-Diffusion-Flux-Splitting Scheme]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201006014]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Low-diffusion-flux-splitting scheme(LDFSS) was combined with weighted essentially non-oscillatory scheme(WENO) to form a hybrid scheme. WENO was used to the reconstruction of physical variables and LDFSS to the splitting of the flux. Riemann problems and inviscid hypersonic blunt body flow were calculated with the hybrid scheme. Also a supersonic turbulent plate boundary-layer was calculated by using hybrid LES/RANS simulation. The results showed that, compared with WENO schemes based on Lax-Fridrichs, the splitting scheme has better resolution on shock and contact discontinuity and better positivity property of scalars and robustness. In the hybrid simulation, the scheme exhibits better prediction of the fluctuating characteristics of the turbulent flow field and statistics of turbulent fluctuating velocities in the hybrid simulation.]]></description>
<pubDate>2012/8/28 16:33:32</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[CHEN Ti,SUN Mingbo,FAN Xiaoqiang,LIANG Jianhan and LIU Weidong]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>CHEN Ti,SUN Mingbo,FAN Xiaoqiang,LIANG Jianhan and LIU Weidong</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201006014]]></guid><cfi:id>571</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[A New Clock Error Control Algorithm of X-Ray Pulsars/SINS Integrated Navigation]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201006015]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[X-Ray pulsars/SINS integrated navigation is one of the effective means to extend the application scope of pulsars navigation, and  it is also a feasible project of the application of pulsars navigation in the future. When the clock error drifts with time, the Pulsars/SINS Integrated Navigation will be affected. In this paper, the clock error is extended as the state variable, thus a new clock error control algorithm of X-Ray pulsars/SINS integrated navigation is proposed. Results show that the new algorithm can well control the clock error and guarantee the navigation precision of pulsars/SINS integrated navigation, so the new algorithm is referable to the application of navigation based on X-Ray pulsars.]]></description>
<pubDate>2012/8/28 16:33:33</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[SUN Shouming,ZHENG Wei and TANG Guojian]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>SUN Shouming,ZHENG Wei and TANG Guojian</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201006015]]></guid><cfi:id>570</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Sufficient Condition and Characteristic Analysis for a Spacecraft Rendezvous with Walker ConstellationSatellites without Orbital Maneuver]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201006016]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Taking Walker constellation as object, the problem of single spacecraft rendezvous with multiple constellation satellites without orbit maneuver was investigated. According to the phase homogeneous character of Walker constellation, the sufficient condition that a spacecraft rendezvous with multiple Walker constellation satellites without orbital maneuver was obtained, followed by the investigation of the problems with rendezvous number and combination of constellation satellites. Furthermore, the orbital design method that can compute spacecraft orbit analytically was presented, and the characteristic of rendezvous orbit was analyzed as well. Finally, the possibility of spacecraft rendezvous with more than three constellation satellites was discussed. The theoretical proof is provided for single spacecraft rendezvous with multiple constellation satellites without orbital maneuver by research findings.]]></description>
<pubDate>2012/8/28 16:33:33</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[ZHANG Jing,XI Xiaoning and WANG Wei]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>ZHANG Jing,XI Xiaoning and WANG Wei</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201006016]]></guid><cfi:id>569</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Research on Dynamic Model of the Capsule's Vertical Landing]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201006017]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Considering the landing field's elastic-plastic characteristic, a model which took the capsule's vertical landing as an elastic-plastic contact problem was established. The numerical simulation indicated that the soil's bearing capability played an important role during the capsule's landing, with the same Young's modulus and Poisson's ratio: when the soil's bearing capability increases, the capsule gets bigger acceleration, less energy loss and higher bounce.]]></description>
<pubDate>2012/8/28 16:33:33</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[GUO Peng,CHENG Wenke and QIN Zizeng]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>GUO Peng,CHENG Wenke and QIN Zizeng</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201006017]]></guid><cfi:id>568</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[The Orthotropic Material Parameters SensitivityAnalysis of Solid Motor Grain]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201006019]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The orthotropic material has been widely applied in large solid motors. In order to reduce the Von Mises strain, and greatly improve the structural integrity of solid motors, the star grain is taken as an example. The orthotropic material parameters sensitivity analysis of elastic modulus and Poisson's ratio of propellant and insulation blanket are studied. The orthotropic material parameters sensitivity coefficients of solid motor grain are obtained. The methods and conclusions are helpful for the designers, manufacturers of solid motors.]]></description>
<pubDate>2012/8/28 16:33:33</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LEI Yongjun<sup>1</sup>,YUAN Duancai<sup>2</sup> and LIN Wenfeng<sup>1</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LEI Yongjun<sup>1</sup>,YUAN Duancai<sup>2</sup> and LIN Wenfeng<sup>1</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201006019]]></guid><cfi:id>567</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Fast Unstructured Mesh Generation Based on Arbitrary Polygon]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201006020]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Mesh reconstruction is the key to the numerical simulation in CFD with large scale moving boundary which contains fast and stable mesh generation arithmetic. Firstly, this framework established efficient initial triangulation arithmetic based on directional edge theory which is fit for arbitrary polygon. Then it proved the arithmetic of longest edge division matches the divergence at some time and closes down the divergence with Delaunay edge swapping. Finally, the paper optimizes mesh with vertex spring model. The results indicate the way established in this study is efficient and stable.]]></description>
<pubDate>2012/8/28 16:33:33</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LIU Feng,FENG Dinghua,DING Guohao,PAN Sha and LI Hua]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LIU Feng,FENG Dinghua,DING Guohao,PAN Sha and LI Hua</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201006020]]></guid><cfi:id>566</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Numerical Simulation of Cellular Detonation Using DifferentChemical Reacting Source Term Methods]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201005001]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[An improved de-coupled solver of non-equilibrium  flow was used to split the Euler equations for a reacting flow. Inviscid flux was calculated with fifth-order WENO scheme. Trapezoid formula and α-QSS methods were applied to deal with the stiffness generated by the chemical reacting source term of species equations separately. Time integration was performed with two-order TVD Runge-Kutta scheme. Cellular detonation of       H<sub>2</sub>/O<sub>2</sub>/Ar in a  straight tube was numerically studied. Calculated results by different methods  were similar, and triple point structures were analyzed. The releasing heat of  chemical reaction dealt with by α-QSSmethod is higher than that by trapezoid formula, so the detonation wave propagating speed of α-QSSmethod is higher than that of trapezoid formula too. Development of cellular structure was elaborated. Due to interactions between transverse waves and between transverse wave and tube wall, re-initiation was ignited, which plays a crucial role in the propagating of detonation wave. Ratio of numerical cellular structure length to width is consistent with reference value, which indicates the feasibility of the numerical method.]]></description>
<pubDate>2012/8/28 16:45:10</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LIU Shijie,LIN Zhiyong,SUN Mingbo and LIU Weidong]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LIU Shijie,LIN Zhiyong,SUN Mingbo and LIU Weidong</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201005001]]></guid><cfi:id>565</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Experimental Investigation of the Starting Performances of the 2-D Supersonic Air Ejector]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201005002]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Supersonic ejector is an important component of the high altitude test facility. Evacuating the test cell before engine start by the ejector can arrest the rocket exhaust leak into the cell, thereby prevent the potential exhaust separation in the rocket nozzle. Meanwhile, the start phase of the ejector is the most critical condition for ejector operation, and an ejector designed improperly will result in an unacceptable high starting pressure and inability to be started of the ejector. In order to investigate the starting performances under this condition, a test facility for small scale supersonic air ejector is constructed. By using pneumatic method and schlieren technology, the flow field is studied when the ejector on utmost starting pressure ratio. The result shows that the utmost starting pressure goes down with the mixing-room contraction ratio. The low mixing-room contraction ratio will cause the ejector unable to be started as well as insufficient ejecting pressure. It is observed that the chamber pressure will go up monotonously with the ejecting pressure when the inability of the ejector is induced by low mixing-room contraction ratio. In contrast, if the ejector unstart is induced by insufficient ejecting pressure, the chamber pressure will go down with the ejecting pressure.]]></description>
<pubDate>2012/8/28 16:45:10</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[CHEN Jian,WU Jiping,LV Huiqiang and WANG Zhenguo]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>CHEN Jian,WU Jiping,LV Huiqiang and WANG Zhenguo</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201005002]]></guid><cfi:id>564</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Research on Multiple-revolution Lambert Problem inSpacecraft Rendezvous]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201005003]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[According to the fixed-time hard rendezvous with chase spacecraft in high eccentric orbit, a new algorithm was introduced to solve      multiple-revolution Lambert problem, which can find the optimal transfer orbit quickly. The solutions of multiple-revolution Lambert transfer problem were researched, and the relationship between transfer time and transfer orbit elements was figured out while the optimal rendezvous problem without time constraint was also studied. The calculation results for fixed-time rendezvous validate the correctness and high-level efficiency of the algorithm.]]></description>
<pubDate>2012/8/28 16:45:10</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[TAN Lifen,YAN Ye,ZHOU Ying and TANG Guojin]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>TAN Lifen,YAN Ye,ZHOU Ying and TANG Guojin</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201005003]]></guid><cfi:id>563</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Characteristic Analysis of Space Rendezvous Trajectory Safety]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201005004]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The trajectory safety characteristic of space rendezvous was studied. First of all, the quantitative performance index of space rendezvous trajectory safety was proposed. The 3σellipsoid of relative position dispersal resulting from the navigation errors and control errors was investigated to describe quantificationally the relative trajectory safety between chaser and target vehicles. And then the orthogonal design of experiment method was adopted to analyze the influence of the transfer time, the number of impulses, and the intervals of impulses on the trajectory safety characteristic. The results show that the transfer time is the most significant among all the factors, the number of impulses is the secondary, and the interval influence is very small. Finally, the influence of initial rendezvous condition was analyzed by numerical simulation, and the results illustrate that -R-bar coplanar rendezvous makes the trajectory safety index the smallest. Furthermore, the influence on fuel consumption was analyzed, and the effect is opposite to that on safety index. The study points out the direction of the design of safe rendezvous trajectory, and provides the way to design the multi-objective optimal rendezvous trajectory.]]></description>
<pubDate>2012/8/28 16:45:10</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LIANG Libo,LUO Yazhong,WANG Hua and TANG Guojin]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LIANG Libo,LUO Yazhong,WANG Hua and TANG Guojin</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201005004]]></guid><cfi:id>562</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Numerical Simulation of Multi-Chip Ball Grid ArrayPackage Under Thermal Loading]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201005005]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Three dimensional parametric finite element analysis models were created for typical high density BGA (Ball Grid Array) package to analyze the structure deformation and stress when loading steady temperature upon packages with different sizes. A simplified model for series analysis including equivalent beam and critical solder ball was established to analyze the effect of design parameters upon the mechanical properties of the package. The numerical results reflected the stress distribution and varying traits of the package, main parameters affecting the deformation and stress were identified. The method developed is convenient and effective. Also it can be applied for analysis of different types of BGA, or can be used for different analysis purpose, and is of certain reference value for the design and optimization of such kind of packages.]]></description>
<pubDate>2012/8/28 16:45:10</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[MAO Jia,JIANG Zhenyu,CHEN Guangnan and ZHANG Weihua]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>MAO Jia,JIANG Zhenyu,CHEN Guangnan and ZHANG Weihua</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201005005]]></guid><cfi:id>561</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Dynamic Modeling and Simulation of a Free-floatingFlexible Manipulator System]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201005006]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Free-floating flexible manipulator system has become a nonholonomic system subject to the constraints of the conservation of angular momentum. The dynamic model of the nonholonomic system is usually the differential algebraic equation which is difficult to solve. So the free-floating system is translated into holonomic system in this research. First, the attitude of carrier was supposed to be controlled by torques. As a result, the system turned to be holonomic because the constraint of the conservation of angular momentum need not be satisfied, and the dynamic equations of the holonomic system were deduced based on Lagrange method. Second, the dynamic equations of free-floating system were obtained by putting the attitude control torques into zero. Finally, the dynamic equations were solved with numerical method. The numerical result is compared with the simulation result in ADAMS and the effective of the model for free-floating flexible manipulator system is verified.]]></description>
<pubDate>2012/8/28 16:45:11</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LIAO Yihuan,LI Daokui and TANG Guojin]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LIAO Yihuan,LI Daokui and TANG Guojin</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201005006]]></guid><cfi:id>560</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Analysis of the Phenomenon of Bull Whipping in the DeploymentProcess of Large Parachute]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201005007]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The bull whipping phenomenon in the deployment process of a large parachute was analyzed. Based on its character, the dynamic model of the whole process was built in five stages. At first, the basic model and restriction model were built respectively. Through their combination, the dynamic model of multibody systems of every stage was built. Then by connecting the dynamic model of five stages, the dynamic model of the entirely deployment process was accomplished. Through analyzing the results of simulation, the canopy displacement and shape, the velocity of top segment canopy, departure distance and tensile force distributing of canopy and lines when forming the bull whipping phenomenon are educed, some important and character data of the bull whipping phenomenon are summarized. The conclusion can provide reference for the engineering design department to designing, improving and using the large parachute.]]></description>
<pubDate>2012/8/28 16:45:11</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[WANG Haitao<sup>1</sup>,QIN Zizeng<sup>1</sup>,SONG Xumin<sup>2</sup>,GUO Peng<sup>1</sup> and TAO Wusha<sup>3</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>WANG Haitao<sup>1</sup>,QIN Zizeng<sup>1</sup>,SONG Xumin<sup>2</sup>,GUO Peng<sup>1</sup> and TAO Wusha<sup>3</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201005007]]></guid><cfi:id>559</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Experimental Study of the Mixing Process of Transverse FuelInjection in the Upper Part of a Cavity]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201005008]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Based on the technology of Nano-based Planar Laser Scattering(NPLS), the ambient flow field of a cavity was studied  in the research, in which the ethene fuel was injected perpendicularly in the upper part of a cavity placed in a scramjet engine model. The study focused on the mixing process of the fuel jet and its mainstream, the comparison of the changes in the fuel jet penetrability under different injection stagnation pressures, as well as the effect of the cavity geometry parameters on the mixing process of the fuel jet and its mainstream. Through the study, the effect of the injection stagnation pressures on the mixing of the fuel jet and its mainstream was found mainly in two aspects: the penetrability and the diffusion of the fuel jet. As for the fuel jet, this study indicated that the main phase of the mixing process with the mainstream begins when the eddies come forth and ends when the eddies break up. Moreover, this study showed that a closer location of the injector helps to produce a better mixing of fuel jet and mainstream and a higher-quality transportation of the fuel jet to the cavity. In addition, the influence of the cavity configuration on the fuel jet primarily starts from the stage of the breaking up of the large-sized eddies.]]></description>
<pubDate>2012/8/28 16:45:11</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[ZHAI Zhenchen,ZHOU Jin and HAN Xu]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>ZHAI Zhenchen,ZHOU Jin and HAN Xu</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201005008]]></guid><cfi:id>558</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[An Adaptive Notch Filter for Solid Launcher Attitude Control System]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201005009]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[An adaptive notch filter design that considers the  body-bending vibration associated with the attitude control of a solid launcher is discussed. The problem of obtaining a notch filter from a given signal was first formulated as the conventional problem of system identification. Then the proposed adaptive notch filter was developed via the algorithm of Steiglitz-McBride. The new adaptive notch filter exhibits fast convergence speed and an excellent capability to frequency tracking in signals. Applying this adaptive notch filter to the launcher results in stable response characteristics of the attitude control system, which is unstable without adaptation.]]></description>
<pubDate>2012/8/28 16:45:11</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LIU Kun and SUN Ping]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LIU Kun and SUN Ping</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201005009]]></guid><cfi:id>557</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[GNSS Autonomous Navigation Integrity Weighted TechniqueBase On Crosslink]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201005010]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Under GNSS autonomous navigation mode, traditional  system cannot support integrity services. Therefore, a GNSS autonomous navigation integrity weighted technique based on crosslink has been developed, using the modified weight matrix of robust M-estimator for crosslink range degrading by failure satellite. Results show that it can ensure autonomous navigation services precision with continuous stable autonomous orbit determination and time synchronization. Simulation of this technique suggests that it can effectively remove effects of autonomous orbit determination by failure satellite, which has the same orbit determination precision of healthy constellation.]]></description>
<pubDate>2012/8/28 16:45:11</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LIN Yiming<sup>1</sup>,CHU Haibin<sup>2</sup> and QIN Zizeng<sup>1</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LIN Yiming<sup>1</sup>,CHU Haibin<sup>2</sup> and QIN Zizeng<sup>1</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201005010]]></guid><cfi:id>556</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Hybrid LES/RANS Simulation of 2D Shock/TurbulentBoundary-layer Interactions]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201004001]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In order to reduce the computational cost of LES for high Reynolds number, a hybrid Large Eddy Simulation/Reynolds-Averaged Navier-Stokes (hybrid LES/RANS) approach which combined two-equation k-ω SST turbulence model and Yoshizawa's one-equation sub-grid scale model with a blending function was developed. The hybrid method together with AUSM<sup>+</sup>-up scheme was conducted to investigate a Mach 2.85 flow field of a 20-degree compression  ramp. The effects of two kinds of inflow boundary conditions (fixed inlet and inlet with super-imposed white noise) were investigated. Separation and reattachment of the boundary layer along with separation shock were obtained from the simulation. The separation zone predicted was significantly larger than the experimental result. Defects of the hybrid method were analyzed and possible improvements were presented.]]></description>
<pubDate>2012/9/6 8:51:59</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[CHEN Ti,SUN Mingbo,FAN Xiaoqiang and LIU Weidong]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>CHEN Ti,SUN Mingbo,FAN Xiaoqiang and LIU Weidong</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201004001]]></guid><cfi:id>555</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Entry Guidance Law Design for Lunar Return Crew Module]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201004002]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Aiming at entry guidance mission of a mooncraft with the second universe velocity more or less, the reentry guidance law which meets various constraints, including G-load, heating and landing site location constraints, was studied. The lunar return crew module is a ballistic-lift vehicle with low lift-to-drag ratio, the strategy calls for controlling the trajectory by modulation of the magnitude and sign of the vehicle's bank angle. The determination of the magnitude of bank angle was formulated as a nonlinear univariante root finding problem, while the sign of the angle was dependent upon the reversals in accordance with the lateral corridor, which was treated as a function of velocity. Integrated dispersions Monte Carlo simulations were performed to evaluate the performance of the proposed approach, and the results show that the downrange standard deviation is about 30 km, and the cross range standard deviation is smaller than 5 km. In addition, the working factors on bank rate are analyzed, and the relation between the feedback gain factor regulation and guidance precision is proposed.]]></description>
<pubDate>2012/9/6 8:51:59</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[SHEN Hongxin,LI Haiyang and PENG Qibo]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>SHEN Hongxin,LI Haiyang and PENG Qibo</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201004002]]></guid><cfi:id>554</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[GNSS Autonomous Navigation Integrity Separation Technique]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201004003]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Under GNSS autonomous navigation mode, in order to keep constellation stabilization and integrity, failure satellites must be separated in time. A GNSS autonomous navigation integrity separation technique was developed, and satellite failure judgment method was analyzed. Satellite failure separation procedures were designed, and then a failure check and separation technique was presented. Simulation of this technique suggests that it ensures services precision by effectively separating failure satellites among autonomous navigation constellation. Furthermore, this technique is not very complex and easy for engineering.]]></description>
<pubDate>2012/9/6 8:51:59</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LIN Yiming<sup>1</sup>,CHU Haibin<sup>2</sup> and QIN Zizeng<sup>1</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LIN Yiming<sup>1</sup>,CHU Haibin<sup>2</sup> and QIN Zizeng<sup>1</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201004003]]></guid><cfi:id>553</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[A Data Fusion Method for Navigation ConstellationAutonomous Navigation Based on X-Ray Pulsar]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201004004]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[To solve the problem of deficiency of rank existing in navigation constellation long-time auto-navigation based on inter-satellite measurement, a method of integrated navigation based on the Inter-Satellite Links (ISL) and X-ray Pulsar was proposed. The fundamentals of this method were described. To rationalize the computational burden, the generalized federated filters were simplified and improved to fuse the measurements based on ISL and X-ray Pulsar. Finally, the simulation was carried out, and the results proved the rationality and feasibility of this method.]]></description>
<pubDate>2012/9/6 8:51:59</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[ZHU Jun<sup>1</sup>,CHEN Zhonggui<sup>1,2</sup>,LIAO Ying<sup>1</sup> and WEN Yuanlan<sup>1</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>ZHU Jun<sup>1</sup>,CHEN Zhonggui<sup>1,2</sup>,LIAO Ying<sup>1</sup> and WEN Yuanlan<sup>1</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201004004]]></guid><cfi:id>552</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Geometric Parameters Sensitivity Analysis for Star GrainBased on Secondary Development of Patran]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201004005]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In order to analyze the effect of geometric parameters on the structural integrity of star grain, the parameterized model of star grain was constructed through PCL(Patran Command Language) on the platform of FM  software MSC.Patran/Nastran. The law of maximum Von Mises strain variation with geometric parameters was studied, and the geometric parameters sensitivity was  analyzed based on the parameterized model. The results show that grain web thickness, star angle coefficient, star-hole number, and the rounding radius of groove top have great effect on the structure integrity of star grain. Therefore, more attention should be paid to these parameters in motor design. The analytical method and conclusion are beneficial for designing SRM.]]></description>
<pubDate>2012/9/6 8:51:59</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[SHEN Zhibin,LI Lei,LEI Yongjun and TANG Guojin]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>SHEN Zhibin,LI Lei,LEI Yongjun and TANG Guojin</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201004005]]></guid><cfi:id>551</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Research on Attitude Control of Kinetic Energy Interceptor under Blended Operation of Lateral Thrust and Aerodynamic Force]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201004006]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[An attitude control method of kinetic energy interceptor under blended operation of lateral thrust and aerodynamic force was developed and a short period movement model of interceptor was presented. A combined control system was designed, using linear quadratic optimal tracking control theory and the fire logic of attitude control missiles. Through analyzing the nonlinear tolerance, a conclusion was drawn that the system has strong robusticity to the thrust bias. Simulation results of attitude control and six-dimension intercept trajectory with lateral jet interaction show that the control method proposed has quick response characteristic and good tracking performance for guidance command, and it can meet the demands of direct interception in the terminal phase.]]></description>
<pubDate>2012/9/6 8:51:59</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[XU Mingliang,LIU Luhua,TANG Guojian and ZHU Longkui]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>XU Mingliang,LIU Luhua,TANG Guojian and ZHU Longkui</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201004006]]></guid><cfi:id>550</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Optimal Design of Conical Cavitator of Supercavitating Vehicles]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201004007]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Different empirical formulae in the calculation of the supercavity shape were analyzed, showing that the Guzevsky formulae has good precision and scope of application. Targeting on reducing the drag, enhancing the cavitation number and enlarging the volume of the supercavitating vehicle, an optimal design model of the conical supercavitator was built based on the Guzevsky formulae. The weight method and genetic algorithm were applied in solving the optimal problem. The results are consistent with the current theory. Effect of aspect ratios, cavitation numbers in the design process were studied. The results indicate that cavitation number is the most important factor that affects the dimension of the supercavity and the volume of the vehicle has been increased significantly through the optimal design process.]]></description>
<pubDate>2012/9/6 8:51:59</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LIN Mingdong,HU Fan and ZHANG Weihua]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LIN Mingdong,HU Fan and ZHANG Weihua</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201004007]]></guid><cfi:id>549</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Comparative Analysis of Two Types of Strap-on LaunchVehicle's Elastic Vibration Modeling Method and the Influenceon Attitude Control System]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201004008]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In view of the different characteristics of modes between long and short strap-on launch vehicles, the differences and relations of elastic vibration modeling method of them were analyzed firstly. Then a new attitude dynamic model of solid strap-on launch vehicle was derived, the elastic vibration equation in the model was also derived by finite element method. Finally, the coupling among three channels based on the new model was studied. Inverse Nyquist Array method was used to design the controller. The results show that the new model can reflect more exactly the coupling characteristics of longitudinal, lateral and torsinal vibration of strap-on launch vehicle. Although the coupling among three channels exists, the coupling matrix has the diagonal dominance characteristics and the controller designed by Inverse Nyquist Array method can obtain a good performance.]]></description>
<pubDate>2012/9/6 8:51:59</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LI Jiawen<sup>1</sup>,LI Enqi<sup>2</sup>,LI Daokui<sup>1</sup> and ZHOU Jianping<sup>1</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LI Jiawen<sup>1</sup>,LI Enqi<sup>2</sup>,LI Daokui<sup>1</sup> and ZHOU Jianping<sup>1</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201004008]]></guid><cfi:id>548</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Effects of the Attached Apex Drogue on Phenomenon of BullWhipping in the Deployment Process of Large Parachute]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201004009]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Based on the finite element thought, a multistage, multi-finite-element and multi-freedom dynamic model of the deployment process of a large parachute was built. The effects of the attached apex drogue and peel off band on the phenomenon of bull whipping formed after the deployment process of the main parachute were studied through simulation. The analysis was focused on the comparison of shape movements of canopy, velocity of bull whipping and distance of departure with or without the attached apex drogue. The conclusion can provide theoretic help for the engineering design department in designing, improving and using the large parachute.]]></description>
<pubDate>2012/9/6 8:51:59</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[WANG Haitao<sup>1</sup>,QIN Zizeng<sup>1</sup>,SONG Xumin<sup>2</sup> and GUO Peng<sup>1</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>WANG Haitao<sup>1</sup>,QIN Zizeng<sup>1</sup>,SONG Xumin<sup>2</sup> and GUO Peng<sup>1</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201004009]]></guid><cfi:id>547</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Technology of Aeroengine Testing Data PreprocessingBased on Robust Kalman Filter]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201004010]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The standard Kalman filter algorithm cannot accurately preprocess the measured data of aeroengine with exceptional errors. The principle of standard Kalman filter and the impact of test errors to the filter estimate results were analysed, and the method of dynamically adjusting the weight of observation information in the filter estimate result was introduced. Then, based on M-estimation theory, the Robust Kalman filter principle and the recursion formula were presented. The state-space equations and observation equations of the measured parameters were established in terms of CA(Constant Acceleration)model. In order to decrease the calculation consumption, the sequence filter was applied separately to process the different sensed data. Furthermore, the preprocessing to the simulation sensed data of a given turbofan engine's steady operation was carried out as an example, using the given Robust Kalman filter. The calculation results, compared with standard Kalman filter, show that the designed Robust Kalman filter has better estimate precision with a given model error.]]></description>
<pubDate>2012/9/6 8:51:59</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[YIN Dawei<sup>1</sup>,LIAO Ying<sup>1</sup>,WANG Lei<sup>2</sup> and LIANG jiahong<sup>2</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>YIN Dawei<sup>1</sup>,LIAO Ying<sup>1</sup>,WANG Lei<sup>2</sup> and LIANG jiahong<sup>2</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201004010]]></guid><cfi:id>546</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Characteristic Analysis and Design of Hybrid Trajectory for MannedLunar Landing Mission Based on Double Two-body Model]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201004011]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Hybrid trajectory is one of the most important trajectory types for manned lunar landing mission. Using the componential characteristic of hybrid trajectory, a hybrid trajectory calculation method based on free return trajectory was proposed under double two-body model. Then, the major characteristics of hybrid trajectory were analyzed, such as energy requirement and time of flight. A little modification was made when calculating the ephemeris of the Moon, in which the Moon motion around Earth was considered as noncircular orbit instead of circular orbit. Finally, a design example was presented while the results of the simulation validate the method proposed.]]></description>
<pubDate>2012/9/6 8:51:59</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[HUANG Wende<sup>1</sup>,XI Xiaoning<sup>2</sup> and WANG Wei<sup>1</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>HUANG Wende<sup>1</sup>,XI Xiaoning<sup>2</sup> and WANG Wei<sup>1</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201004011]]></guid><cfi:id>545</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Investigation of Dual Time-step Approach for Supersonic Combustion Flow]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201003001]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[A dual time-step approach was developed for simulation of unsteady supersonic combustion flow. The flow and reaction were separately calculated with a time-splitting method. The flow equations were solved by the dual time-step approach with the inner iteration proceeded by a LU-SGS method. The source equations were solved by 2<sup>nd</sup>order trapezoidal formulas. The influences of the time-splitting scheme and the time step were studied. The results show that the 1st order time-splitting can slightly overestimate the chemical efficiency and a 2<sup>nd</sup>order time-splitting should be implemented. The time step has a significant effect on the results. In order to ensure the computational precision of the uncoupled method, the time step should be kept small enough so that the unsteady behaviors of the large scale vortices, which dominate the transport processes in the flow, can be captured accurately.]]></description>
<pubDate>2012/9/6 8:52:14</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[WANG Hongbo,SUN Mingbo,WU Haiyan and WANG Zhenguo]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>WANG Hongbo,SUN Mingbo,WU Haiyan and WANG Zhenguo</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201003001]]></guid><cfi:id>544</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Modeling Research of Influence on Docking CombinedSpacecraft's Initial Attitude]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201003002]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Analytical and numerical models of influence of docking process on combined spacecraft's initial attitude were developed. Based on the theorem of angular momentum with respect to total centroid, the general expression of numerical model for combined spacecraft's attitude angular velocity was obtained. By combining chase spacecraft's absolute motion with target spacecraft's relative motion equations, numerical model based on docking dynamics was developed. Finally, combined spacecraft's attitude angular velocity was contrasted with analytical and numerical models on different cases of single-error and multi-error. The results show that absolute error is within 0.07°/s and relative error is less than 10 percent between two models. Additionally, applicable phases of two models for engineering missions are presented.]]></description>
<pubDate>2012/9/6 8:52:14</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[HUANG Haibing,LI Haiyang,WANG Hua and TANG Guojin]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>HUANG Haibing,LI Haiyang,WANG Hua and TANG Guojin</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201003002]]></guid><cfi:id>543</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[A New Method for Similar Multi-target Detection Based onShape Entropy Difference]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201003003]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In order to realize auto target detection of multi-target image of shooting ranges, the similarity of targets' shape was utilized, and a new method for auto similar target detection based on shape entropy difference was proposed. First, the concept of shape entropy difference was presented, which merged shape information into the calculation of entropy, and the target was detected by searching for the extreme point of entropy difference. Then, an auto target detection method based on shape entropy difference was realized. Finally, the validity and robustness of the algorithm was approved by experiment. Compared with the common algorithms of target detection, the method proposed here has better tolerance capability against noise and illumination variety. The method can be used for target detection of image of shooting ranges and other similar applications.]]></description>
<pubDate>2012/9/6 8:52:14</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[WANG Kunpeng,ZHANG Xiaohu,ZHU Zhaokun and YU Qifeng]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>WANG Kunpeng,ZHANG Xiaohu,ZHU Zhaokun and YU Qifeng</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201003003]]></guid><cfi:id>542</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Numerical Study on a Ramjet Combustor with Center Preburner]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201003005]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[A ramjet with a center preburner was designed for the purpose of intensifying the ability of ignition and flamehold characteristic at low pressures. The numerical studies were conducted to investigate the spray and combustion characteristics in the simplified model combustion. The result reveals that, with the change of the work conditions, the convergent rear of the preburner has a different impact on the interaction between the inner and the outer flow. The flow at the entrance of the preburner will accelerate due to the increase in the pressure drop and combustion occurring downstream affects the flow characteristics in the preburner.]]></description>
<pubDate>2012/9/6 8:52:14</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[XI Wenxiong,TAN Jianguo and WANG Zhenguo]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>XI Wenxiong,TAN Jianguo and WANG Zhenguo</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201003005]]></guid><cfi:id>541</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Precision Analysis of Early Warning SystemInfluenced by Space-based LOS Measurement Error]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201003006]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In order to reduce influence on early warning results caused by the system error in the early warning system, the calibration to the instrument must be carried on. So it is necessary to discuss the line of sight measuring error farther. This article theoretically discussed the sight error influence on early warning results, including trajectory launch point, trajectory course, and trajectory falling point, and found that the most important influence factor was frequency change. Based on the constant error, linearity error and periodicity error, the corresponding simulation was given to provide the support for the geometry calibration plan.]]></description>
<pubDate>2012/9/6 8:52:14</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[QIANG Sheng<sup>1</sup>,SHEN Zhen<sup>1</sup>,CHENG Hongwei<sup>2</sup> and YI Dongyun<sup>1</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>QIANG Sheng<sup>1</sup>,SHEN Zhen<sup>1</sup>,CHENG Hongwei<sup>2</sup> and YI Dongyun<sup>1</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201003006]]></guid><cfi:id>540</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Study of Betterment Arithmetic of Ambiguity inAbsolution Position Based on X-ray Pulsar]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201003007]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The absolution navigation based on X-ray pulsar is an entirely new autonomous technology. This paper put forward the basic theory of absolution navigation based on pulsar, and proposed a bettered algorithm of integer cycle ambiguity in the method of absolution navigation. Then the algorithm was analyzed deeply and the theoretical derivation was made. Through the simulation solution of ambiguity and position of spacecraft, it can achieve ideal precision. This cycle ambiguity arithmetic provides a new avenue for absolution navigation based on X-ray pulsar.]]></description>
<pubDate>2012/9/6 8:52:14</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[GUI Xianzhou,LI Shengliang and LI Zhihao]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>GUI Xianzhou,LI Shengliang and LI Zhihao</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201003007]]></guid><cfi:id>539</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Combustion Study of Condensed Carbon Particle in the SecondaryCombustion Chamber of Solid Rocket Ramjet]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201003008]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The effect of pressure and temperature on carbon particle combustion was studied by an improved Moving Flame Front (MFF) model. On the basis of the above discussion, the carbon particle combustion in solid rocket ramjet was analyzed. As a result, the carbon particle combustion mechanism in solid rocket ramjet was achieved. Moreover, numerical results were validated by direct-connect test of solid rocket ramjet. The result shows that most of carbon particle in the secondary combustion chamber burned near the inlet exit.]]></description>
<pubDate>2012/9/6 8:52:14</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[WANG Dequan,XIA Zhixun and HU Jianxin]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>WANG Dequan,XIA Zhixun and HU Jianxin</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201003008]]></guid><cfi:id>538</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Preliminary Aerocapture Trajectories Design for MannedMars Mission]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201003009]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In view of human exploration of Mars, the three-degree-of-freedom dynamic model of aerocapture trajectory was established. The constraints which satisfy the mission requirements were listed, and the entry corridor was obtained. The influence of some parameters on the trajectory shape was analyzed. A pipelining optimization approach of Genetic Algorithm(GA) and Sequential Quadratic Programming(SQP) were introduced to analyze the attainable region of flight through bank angle control. The results indicate that, compared with direct deceleration by retro-rocket, aerocapture mode is highly advantageous in energy requirement, and has good maneuver ability. It is a feasible approach for manned spacecraft to insert into Mars orbit.]]></description>
<pubDate>2012/9/6 8:52:14</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LI Zhen,LI Haiyang and CHENG Wenke]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LI Zhen,LI Haiyang and CHENG Wenke</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201003009]]></guid><cfi:id>537</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Researches Into Gray Value Transform to Improve SceneMatching Robustness]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201003010]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Scene match arithmetic which has high dependability and precision is the most important factor of image navigation for independent navigation aircraft. The current study has researched into gray distortion of scene match images, and brought forward the emendation method based on the histogram similar transform which can improve the veracity and reliability of scene matching arithmetic. For different external condition and imaging apparatus, there are many gray differences in images participating in scene match, which will affect the scene match robustness seriously. Via adjusting the histogram of scene match images to make them identical, this research eliminated the gray distortion. As a result, the scene match images histogram similar coefficients were all more than 0.95. 10 300 true outfield scene matching orientation experimentations  have testified that the pretreatment method for gray images based on histogram  can effectively eliminate the gray distortion and decrease the repetitious patterns caused by gray distortion. The success ratio of scene match has reached the level of 99.98%, which has met the high dependability need of projects.]]></description>
<pubDate>2012/9/6 8:52:14</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LIU Xiaochun,YU Qifeng and LEI Zhihui]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LIU Xiaochun,YU Qifeng and LEI Zhihui</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201003010]]></guid><cfi:id>536</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Fuzzy Reliability-growth Model Analysis Based onDirichlet Prior Distribution]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201003030]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[A fuzzy reliability growth model was presented on the basis of a Bayesian reliability-growth model based on Dirichlet prior distribution using fuzzy theory. The method for determining prior parameters was studied using Dirichlet prior distribution. A metal/water reaction ramjet's reliability growth test data was analyzed using this distribution. The prior distribution and the posterior distribution at each test stage were presented. And the effect of the parameter related to prior information's variance on posterior reliability was analyzed. Fuzzy variable was introduced in the original model to build a fuzzy reliability growth model. Using the model, the fuzzy reliability at each stage was calculated.]]></description>
<pubDate>2012/9/6 8:52:16</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LIU Jitao,HU Fan and ZHANG Weihua]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LIU Jitao,HU Fan and ZHANG Weihua</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201003030]]></guid><cfi:id>535</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Structural Design Optimization of Satellite Central Column Shell]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201002001]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The parameterized analysis model for a composite material central bearing column shell satellite platform was established using FEM software, and the analysis model for central composite column shell was then simplified according to the calculated vibration modes of the satellite platform. The central shell's structural optimization was performed under several design constraints, such as strength, displacement, vibration and buckling. Some design scenarios were calculated and compared, and the work done in this paper will be of reference value for structure design related.]]></description>
<pubDate>2012/9/19 9:01:22</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[MAO Jia,JIANG Zhenyu,CHEN Guangnan and ZHANG Weihua]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>MAO Jia,JIANG Zhenyu,CHEN Guangnan and ZHANG Weihua</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201002001]]></guid><cfi:id>534</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Optimization of Configuration of the Hatch Closure Hingesof the Rear Entry Spacesuit Used for EVA]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201002002]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Based on the finite element method, the strength and stiffness of spacesuit hatch closure under internal pressure are calculated. The optimization model of the hinges configuration is established to reduce residual internal force of the hinges. An improvement configuration of the hinges is obtained. The results demonstrate that the optimal configuration of the hinges of the irregular shaped pressure vessel can reduce the residual internal force as a result of the structural plastic deformation.]]></description>
<pubDate>2012/9/19 9:01:22</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[ZHOU Shiming,LI Daokui and TANG Guojin]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>ZHOU Shiming,LI Daokui and TANG Guojin</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201002002]]></guid><cfi:id>533</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Study on Hamiltonian Dynamic Model and Solving Method ofDistributed Satellite System Relative Motion]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201002003]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The Hamiltonian dynamic model of distributed satellite system(DSS)relative motion under earth oblateness perturbation was introduced, and the Hamilton's equation of DSS relative motion was also obtained. Aiming at solving relative two-point boundary value problems of DSS under earth oblateness perturbation, a shooting method based on solving generating function was proposed. High precision formation adjusting problems of DSS under earth oblateness perturbation was calculated. Results demonstrate that the algorithm has high computational efficiency and can avoid the problem of dimension disaster.]]></description>
<pubDate>2012/9/19 9:01:22</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[ZHANG Yuedong,CHEN Qifeng and DAI Jinhai]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>ZHANG Yuedong,CHEN Qifeng and DAI Jinhai</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201002003]]></guid><cfi:id>532</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Two-stage Successive Genetic Algorithm for Space andGround TT&C Scheduling]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201002004]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[A two-stages successive genetic algorithm was used to optimize the scheduling of TT&C (Tracking Telemetry and Command) resource from space and land. Because the object was somewhat separable, the scheduled time windows were separated into two sections. After the population from first section was evolved, the gained optimized solution was combined with the second section, and then the evolution of second phase goes further. For lessening the local searching limitation, virtual time windows were set with some probability in the fitness computation process of first phase, which could retain the individuals that might be the component of overall optimization solution. Simulation demonstrates the proposed method can get good solution at the cost of less time.]]></description>
<pubDate>2012/9/19 9:01:22</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[CHEN Feng and WU Xiaoyue]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>CHEN Feng and WU Xiaoyue</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201002004]]></guid><cfi:id>531</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[The Influence and Correction of Satellite-to-groundRange Variation on Two-way Time Comparison between Satellite andGround Station Clocks]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201002005]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Satellite and ground station time synchronization is the key technology of navigation satellite system. Two-way time comparison method between satellite and ground station clocks can improve the accuracy of satellite and ground station time synchronization effectively. By analyzing the influence of satellite-to-ground station range variation on two-way time comparison, which is the source of hundred nanoseconds error, a method of observe data differential correction was presented. Numerical simulation performed later shows that this method can reach the level of nanosecond precision.]]></description>
<pubDate>2012/9/19 9:01:22</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[WANG Wei,WEI Lidong and FAN Guoqing]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>WANG Wei,WEI Lidong and FAN Guoqing</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201002005]]></guid><cfi:id>530</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Axial Stage Separation with Close-loop Attitude Control ofa Small Solid Launcher]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201002006]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[A low-cost small solid launcher using both lateral jets and gird fins for its attitude control purpose was designed. According to the layout of the vehicle, this paper designed a cold separation scenario to which a close-loop attitude control scheme is introduced. Based on the description of the separation process, dynamic and kinematic equations were built. Meanwhile the ejector piston model, retro-rocket model, aerodynamic model and attitude control model were also established. The collision detection method was discussed and Monte Carlo simulation was introduced to deal with the uncertainties. Simulation results show that the proposed project can not only reduce the attitude deflection of the vehicle but also avoid interstage collision, so it provides a possible choice for the stage separation of this type of vehicles.]]></description>
<pubDate>2012/9/19 9:01:22</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[SUN Ping and LIU Kun]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>SUN Ping and LIU Kun</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201002006]]></guid><cfi:id>529</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Free-return Trajectory and Hybrid Trajectory Design forManned Lunar Landing Missions]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201002007]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The method to design lunar free-return trajectory and hybrid trajectory was studied. The sectional perturbational high precision dynamical model was established, then the search variables, target parameters and differential correction algorithm were designed, and a nominal free-return trajectory was searched out, which was validated and three-dimensionally simulated by STK. In addition, the error transfer was analyzed. The paper described a typical design procedure of hybrid trajectory which combines free-return trajectory and non-free-return trajectory, and simply analyzed the advantages and disadvantages of it. The method and conclusions in the paper can be applied to conceptual design of manned lunar landing mission and trajectory design of the later stage of China Lunar Exploration Program, as well as trajectory design of micro lunar probe launched together with other spacecrafts.]]></description>
<pubDate>2012/9/19 9:01:23</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[BAI Yuzhu,CHEN Xiaoqian and LI Jinghao]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>BAI Yuzhu,CHEN Xiaoqian and LI Jinghao</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201002007]]></guid><cfi:id>528</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[The Application of BOS in Flow Measurement]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201001001]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Background oriented schlieren (BOS) is a new technique for flow visualization. Compared with schlieren and interferometry, BOS can measure density gradient quantitatively with high spatiotemporal resolution. Based on its principle, a BOS system is set up in this paper. Using this system, the thermal convection flow field over a candle flame is measured, and its transient flow structure is visualized. The whole process verifies the performance of the BOS system. Then, a supersonic mixing layer is studied, its fine flow structures and quantitative density gradient distribution are acquired. The results show obvious advantages of BOS in flow measurement.]]></description>
<pubDate>2012/9/19 9:01:35</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[HE Lin,YI Shihe,ZHAO Yuxin,TIAN Lifeng and CHENG Zhongyu]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>HE Lin,YI Shihe,ZHAO Yuxin,TIAN Lifeng and CHENG Zhongyu</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201001001]]></guid><cfi:id>527</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Method of Ray Tracing through Shock Wave Flow Field]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201001002]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In the high speed flow field, shock wave will cause obvious aero-optics effect, which can induce the excursion and focusing of the ray and so on. In this paper, the relationships of angle excursion and shock intensity are reviewed theoretically in the condition of different incidence angles. In application to actual problem, the shock field is usually simulated by computational fluid dynamics. In order to trace the ray through the simulated shock field, an idea and the matched method are carried out, which can improve the tracing precision. In this way, the tracing step distance is aimed to be self-adaptive to local refraction index gradient and grid geometry scale. At last, the ray tracing method is validated. The result shows that the method has high precision for ray tracing in the shock field.]]></description>
<pubDate>2012/9/19 9:01:35</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[FENG Dinghua,PAN Sha,TIAN Zhengyu and LI Hua]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>FENG Dinghua,PAN Sha,TIAN Zhengyu and LI Hua</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201001002]]></guid><cfi:id>526</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Fault Detection Method Based on Cloud-neural Networkof Liquid-propellant Rocket Engine]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201001003]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The fault detection method based on cloud-neural network of LRE (liquid-propellant rocket engine) is studied and realized with fault detection principle. The training results, testing results and fault detection results of the method are given. The method is validated by historical test data. There is no false alarm and missing alarm during testing and validation.]]></description>
<pubDate>2012/9/19 9:01:35</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[HUANG Qiang and WU Jianjun]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>HUANG Qiang and WU Jianjun</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201001003]]></guid><cfi:id>525</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Comparison of Thrust Vector Control Scheme for Solid LaunchVehicle Based on Launching Capability Evaluation]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201001004]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The thrust vector control schemes for solid launch vehicle were compared from the view of launching capability. Three multiple-stage solid launch vehicle schemes with different thrust vector control systems were designed, the ascent trajectory of launch vehicle was optimized by combining augmented lagrangian method with Powell method, and the evaluation results of launching capability were provided. Research results show that, with the same    take-off mass of 50000 kg and object orbit of 300km SSO, the scheme using jet thrusts and grid vane achieved heavier lauching capability, 115 kg bigger than the scheme using vectored nozzle, and 70 kg bigger than the scheme using jet thrusts and jet vane, respectively. All the above can provide theoretic reference for scheme demonstration of solid launch vehicle.]]></description>
<pubDate>2012/9/19 9:01:35</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[YANG Xixiang,JIANG Zhenyu and ZHANG Weihua]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>YANG Xixiang,JIANG Zhenyu and ZHANG Weihua</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201001004]]></guid><cfi:id>524</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Research on Initial Orbit Determination of Cislunar TransferTrajectory with Space-based Angle Measurements]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201001005]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Initial orbit determination of cislunar transfer trajectory with space-based angle measurement is discussed. The measurement platforms include a single satellite and two constellation satellites. First, the smoothness of noise is studied. Second, the effects of arc length and measurement geometry on the orbit determination precise are analyzed. Finally, the disposal of model errors is addressed. According to the research, the constellation synchronized orbit determination is preferred for the initial orbit determination of cislunar Transfer Trajectory.]]></description>
<pubDate>2012/9/19 9:01:35</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LIU Lei and XIANG Junhua]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LIU Lei and XIANG Junhua</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201001005]]></guid><cfi:id>523</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Aerodynamic Parameter Estimation of Large Parachute Based onGenetic Algorithm]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201001006]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The six degrees of freedom dynamic and motion models of the parachute recovery system were built. In order to solve the problem caused by the lack of measurable experiment data, the genetic algorithm was designed to estimate the aerodynamic parameters of the parachute. Simulation result validates the feasibility of the estimation method and the validity of the estimation model. The aerodynamic parameters of a large ringsail parachute applied to manned spacecraft were estimated through the genetic algorithm and the analysis data from the videos of airdrop test. Furthermore, the stability of the ringsail parachute was analyzed through the estimation results. The conclusion can provide theoretical reference for the design of recovery system.]]></description>
<pubDate>2012/9/19 9:01:35</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[WANG Haitao and QIN Zizeng]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>WANG Haitao and QIN Zizeng</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201001006]]></guid><cfi:id>522</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Research on Ambiguity Dynamic Resolution Using DualFrequency Single-epoch Data]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201001007]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[According to the application of GPS differential precise navigation, an ambiguity resolution algorithm is presented. The mathematical model is set up using observations of wide lane double differential carrier phase and double differential pseudorange. In order to make float ambiguity uncorrelated completely, float transformation matrix is constructed by Cholesky decomposition and the integer ambiguity search space is deduced. The criterion of least square residual is used to obtain single-epoch integer ambiguity, OVT (over-the-time) method is applied to verify the consistency of integer ambiguity at different epochs. Experimental results indicate that the mean square deviation of observations has great effect on integer ambiguity's search space and success rate, and the integer ambiguity can be determined correctly and reliably by OVT testing.]]></description>
<pubDate>2012/9/19 9:01:35</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[MENG LingPo and WU Jie]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>MENG LingPo and WU Jie</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201001007]]></guid><cfi:id>521</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Performance Reliability Modeling and Estimation for SpaceBearing under Small Sample Circumstance]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201001025]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[There are small sample and zero failure characteristics in space bearing reliability modeling and analysis. Although performance reliability method may be available, insufficient performance data are still impediments. In the paper, a hierarchy Bayes modeling and analysis method is presented to solve the difficulties under small sample circumstance. Based on failure mechanism analysis, a performance degradation model is built at first. Then multiple methods and information including bootstrap method, experiment data, physics model and expert experience are utilized to determine the Bayes prior distribution. The Bayes calculation problem is settled using MCMC method. Example analysis shows that the method provided in the paper is well applicable, and is an effective method solving reliability modeling and analysis problem of long life products under small sample condition.]]></description>
<pubDate>2012/9/19 9:01:36</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[JIN Guang]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>JIN Guang</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201001025]]></guid><cfi:id>520</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Application of Microthrusters of Integrated Orbit and Attitude Control of Inner-formation Gravity Field Measurement Satellite]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201106015]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The inner-formation gravity field measurement satellite was proposed to measure Earth's gravity field with high accuracy and spatial resolution through precise orbit determination and relative state measurement. Both techniques relied on precise formation control and accurate attitude control, during steady-state phase, where the relative displacement had to be suppressed down to centimeter, and the outer-satellite attitude had to be earth-oriented with 0.1 degree accuracy. The integrated orbit and attitude control aims to guarantee the scientific measurement during steady-state phase, applying micro-thrusters. The all-propulsion design was processed on a coupled linear model with thruster layout; the integrated orbit and attitude control was implemented based on model predictive control (MPC) algorithm. Simulation results demonstrate the feasibility and validity of this integrated control scheme with micro-thrusters.]]></description>
<pubDate>2012/9/12 11:15:10</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[JI Li,LIU Kun and XIANG Junhua]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>JI Li,LIU Kun and XIANG Junhua</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201106015]]></guid><cfi:id>519</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Study of Spacecraft Aeroassisted Coplanar Orbital Transfer Based on Gauss Pseudospectral Method]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201106016]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[It is well known that the use of aeroassisted orbital transfer can save fuel efficiently, thus representing one of development trends of new orbital transfer technology. This paper is concerned with the problem of coplanar orbital transfer of spacecraft from high earth orbit to low earth orbit based on Gauss pseudospectral method (GPM). With the consideration of heating rate limit and control constraints, sub-optimal trajectory of spacecraft’s flight in atmosphere was obtained. On the analysis of trajectory characteristic the first-order necessary optimality conditions of optimized results was demonstrated. Indirect method was also adopted to solve the problem, then the calculation results of the two methods were compared. Simulation results show that it is a simple way to handle constraints with GPM, and it has high precision solutions and can overcome the disadvantages of the indirect method, such as initial value sensitivity and poor robustness. Therefore, GPM is suitable to be applied in the problem of atmospheric spacecraft trajectory optimization.]]></description>
<pubDate>2012/9/12 11:15:10</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[FU Jun,CAI Hong and LI Anliang]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>FU Jun,CAI Hong and LI Anliang</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201106016]]></guid><cfi:id>518</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Numerical Simulation on Temperature and Stress Fields of Two-layered Shell Irradiated by the Intensive Laser Beam]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201106017]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The thermal dynamic response of structures irradiated by the intensive laser beam has been an important issue in the area of laser application. Adopting three-dimensional finite element model, numerical simulation and analysis were performed in order to make out the temperature, stress and displacement fields of two-layered cylindrical shell irradiated by intensive laser beam. In the study, the several parameters of materials corresponding to temperature were considered as variables. The influence on distribution of temperature field brought by various laser spot diameters was also studied. And the rules of temperature rise, stress and displacement of inner layer at the spot center were investigated, while the outer layer’s thickness, expansion factor, the elastic modulus and the Poisson ratio were changing. It is shown that, the diameter of laser spot plays an important role in the temperature field distribution, keeping in touch with conductivities of outer layer; expansion factor is the dominant parameter affecting stress field, thickness is a lesser dominant one, and elastic modulus and Poisson ratio are the least. The conclusion can provide a substantial reference for the laser breakage analysis and anti-laser reinforcing technology.]]></description>
<pubDate>2012/9/12 11:15:11</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LEI Yongjun<sup>1</sup> and WU Fei<sup>2</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LEI Yongjun<sup>1</sup> and WU Fei<sup>2</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201106017]]></guid><cfi:id>517</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[The Investigation of Matching of Injectors andFlameholder in High Speed Airflow]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201106022]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Based on the flow characteristics of ramjet combustion chamber, combustion characters match of the flameholder and injectors is investigated by means of photography of using OH spontaneous radiation，and the two-phase flow numerical simulation. The influence of distance between the flameholder and the injectors on the fuel-air equivalence ratio distribution behind the flameholder is analyzed. The experiment results indicate that the space between the flameholder and injectors has signiticant influence on the reaction flow. When the space between the flameholder and injectors increased, the flame was closed  to flameholder. And the flame flashed back when the velocity of air was low. when the space between the flameholder and injectors shortened, the flame flash back could avoided and the lift-off distance of the flame became small. The flame located close to the flameholder was due to improved vaporization and mixing at a big space between the flameholder and injectors.]]></description>
<pubDate>2012/9/12 0:00:00</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[DUAN Xiaolong<sup>1</sup>,MAO Genwang<sup>1</sup>,MA Tianju<sup>2</sup> and HONG Liu<sup>2</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>DUAN Xiaolong<sup>1</sup>,MAO Genwang<sup>1</sup>,MA Tianju<sup>2</sup> and HONG Liu<sup>2</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201106022]]></guid><cfi:id>516</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Numerical Simulation of Shock-induced Combustion with a New Uncoupled Algorithm in Unstructured Finite Volume Method]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201106025]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[A new uncoupled algorithm of simulating chemical non-equilibrium flow originally realized by finite difference method was extended to the unstructured finite volume method, which makes the simulation of reaction flow in complex configurations possible. The H<sub>2</sub>/Air shock-induced oscillating combustion experiment conducted by Lehr was simulated, and the computed oscillating frequencies conformed well with the ones acquired by experiment, which indicates that the present method is temporally and spatially second order accurate. It is also demonstrated that geometrical configuration plays a definitive role in the combustion regime. If the truncated angle is less or equal to 15 degrees, high frequency oscillating combustion in regular regime occurs, while if the angle is larger or equal to 20 degrees, low frequency oscillating combustion in large-disturbance regime is observed.]]></description>
<pubDate>2012/9/12 11:15:11</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LIU Yu<sup>1</sup>,LIU Jun<sup>1</sup> and BAI XiaoZheng<sup>2</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LIU Yu<sup>1</sup>,LIU Jun<sup>1</sup> and BAI XiaoZheng<sup>2</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201106025]]></guid><cfi:id>515</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Engineering Application on Multidisciplinary Design Optimization of Flight Vehicles]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201105001]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Multidisciplinary Design Optimization (MDO) of flight vehicles is now a focus of international research in the aerospace field. The engineering application research of MDO, however, falls behind the fundamental theoretical research domestically, which sometimes even leads to the suspicion of the practicability of MDO. On the basis of our research on MDO in the past decade, the difficulties of the engineering application and the relevant key technologies of MDO were analyzed. The international research on engineering application of MDO can be approximately summarized into three stages, the characteristics of which were illustrated with three application examples in flight vehicle design implemented by our group. Finally, the future trends of the MDO engineering application were briefly analyzed.]]></description>
<pubDate>2012/8/28 11:51:54</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[CHEN Xiaoqian,YAO Wen,WEI Yuexin and ZHAO Yong]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>CHEN Xiaoqian,YAO Wen,WEI Yuexin and ZHAO Yong</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201105001]]></guid><cfi:id>514</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Uncertainty-based Multidisciplinary Design Optimization of Fractionated Modularized Cluster Spacecraft]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201105002]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The Uncertainty-based Multidisciplinary Design Optimization (UMDO) method was studied for the conceptual design of fractionated modularized cluster spacecraft (fractionated spacecraft), so as to comprehensively assess and optimize life cycle cost, benefit, system robustness and flexibility under uncertainty. Firstly, the UMDO methodology was introduced, as well as the schematic flowchart of UMDO for the fractionated spacecraft conceptual design. Secondly, the system architecture and assessment criteria of the new concept fractionated spacecraft were explained. The disciplinary models, cost models and benefit models were described, and the uncertainties thereof were modeled with probability theory. Thirdly, a notional earth observatory fractionated spacecraft was used as an example to demonstrate the application of UMDO in the fractionated spacecraft conceptual design. The UMDO problem formulation and UMDO procedure organization were presented in detail. The results show that the mean of the net revenue and its robustness under uncertainty can be greatly improved, which verified the effectiveness of UMDO method for fractionated spacecraft conceptual design.]]></description>
<pubDate>2012/8/28 11:51:54</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[YAO Wen<sup>1</sup>,CHEN Xiaoqian<sup>1</sup>,HUANG Yiyong<sup>1</sup> and Michel vanTooren<sup>2</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>YAO Wen<sup>1</sup>,CHEN Xiaoqian<sup>1</sup>,HUANG Yiyong<sup>1</sup> and Michel vanTooren<sup>2</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201105002]]></guid><cfi:id>513</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[An Improved MDO Procedure: Hybrid Bi-Level Integrated System Synthesis]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201105003]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[An improved MDO procedure for BLISS 2000 (Bi-Level Integrated System Synthesis 2000), which is named HBLISS (Hybrid BLISS) to find a way out of a difficulty in applications because of the weighting factor, is proposed. The basic algorithm structure of BLISS 2000 was kept and the weighting factor was cancelled, in which the minimum residual error of coupled variables was utilized to coordinate system level optimization and sub-system level optimization. The algorithm structure and flowchart were introduced. The results of Reducer optimization problem show that HBLISS has the superiority in the disciplinary autonomy and convergence, and the improvement is valid.]]></description>
<pubDate>2012/8/28 11:51:54</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[ZHAO Yong,YANG Weiwei,HUANG Yiyong and WANG Zhenguo]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>ZHAO Yong,YANG Weiwei,HUANG Yiyong and WANG Zhenguo</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201105003]]></guid><cfi:id>512</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Neighborhood Strengthened Concurrent Subspace Optimization Based on Response Surface]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201105004]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[A neighborhood strengthened CSSO-RS is proposed to improve the disadvantages of the Concurrent Subspace Optimization based on Response Surface (CSSO-RS). This algorithm gives rise to an optimization between the system level optimization and subspace level optimization, which greatly improves the coordination affection between these two levels. The optimization region of this algorithm is the neighborhood of the optimal solution obtained by the subspace optimization, and all the design variables are involved in this optimization. The classical test function and an aircraft concept sizing problem were tested, and the efficacy of the algorithm was proved.]]></description>
<pubDate>2012/8/28 11:51:54</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[OUYANG Qi,CHEN Xiaoqian and HUANG Yiyong]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>OUYANG Qi,CHEN Xiaoqian and HUANG Yiyong</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201105004]]></guid><cfi:id>511</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Approximation Based Combined Optimization Methodology]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201105005]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Aimed at solving the problem of optimization convergence and the global optimization, this research proposes a Combined Optimization Methodology, which combines the global and local optimization methods. The former one can obtain global optimum solution but converge slowly, while the latter one can converge fast and obtain a local optimum solution and can be sensitive to initial value. Firstly, the approximation function of the original problem was built. Then the approximate optimum solution was obtained by the global optimization method. The approximate optimum was taken as the initial value, and the real optimum solution is obtained by the local method optimizing the original problem directly. In order to achieve better approximation, the RBF was improved and Shape Parameter Optimization Radius Basis Function was developed by using the surrogate model. Both of the methods were used in the near space aircraft wing optimization. Results show that the modified interpolation method is more accurate than the Kriging model, and the Combined Optimization can obtain the optimum and improve the convergence speed.]]></description>
<pubDate>2012/8/28 11:51:54</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Wei Yuexing,Chen Xiaoqian and Yan li]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Wei Yuexing,Chen Xiaoqian and Yan li</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201105005]]></guid><cfi:id>510</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Energy Function Based Evaluation Method of the GeneralizationAbility of Interpolated-based Surrogate Model]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201105006]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The characteristics of interpolated-based surrogate model were analyzed. The oscillation characteristics of interpolated-based surrogate model, an important factor that affect the generalization capacity was put forward. Analysis shows that: when the oscillation of surrogate model is violent, its generalization ability is weak. An evaluation method based on energy function was put forward to evaluate the generalization ability of surrogate model. By calculating the surrogate model’s first and second derivatives, Energy Function Method (EFM) can obtain the oscillation characteristics of surrogate model. The higher the Energy Function, the more serious the oscillation of surrogate model. Thus its generalization ability is worse. Test functions were made, and the results show that the Energy Function Method is efficient in evaluating the generalization ability of the surrogate model.]]></description>
<pubDate>2012/8/28 11:51:54</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[ZHU Xiongfeng,LUO Wencai and WEI Yuexing]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>ZHU Xiongfeng,LUO Wencai and WEI Yuexing</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201105006]]></guid><cfi:id>509</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Mutative Scale Immune Clonal Selection AlgorithmBased on Multi-population]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201105007]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Mutative Scale Immune Clonal Selection Algorithm (MSICSA) based on Multi-population is proposed. In the algorithm, the dominant position of global optimal solution was highlighted by the nonlinear scale transformation of objective function. Memory sub-population was extracted to exchange information between populations. Antibody population was divided into elite, normal and inferior sub-population. To enhance local and global search capabilities of MSICSA, adaptive Gaussian and uniform mutation were applied to elite and normal sub-population respectively and the inferior antibody was extinguished and replaced by new ones. By introducing the niche technology to increase the diversity of population distribution, the algorithm can prevent premature. Test functions and a space antenna optimization were tested. The results show that the optimization capability of MSICSA is more advanced than CLONALG and SGA, and the computational complexity is reduced.]]></description>
<pubDate>2012/8/28 11:51:54</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[GUO Zhongquan,WANG Zhenguo and YAN Li]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>GUO Zhongquan,WANG Zhenguo and YAN Li</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201105007]]></guid><cfi:id>508</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[ubspace Decomposition and Discarding Optimization]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201105008]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[A new MDO algorithm named as Subspace Decomposition and Discarding Optimization (SDDO) is advanced here. The optimization is based on the approximation model, of which the main idea is based on the subspace decomposition and discarding. Firstly, the approximation model of a MDO problem was carried on its design space. If the precision of approximation model reaches a satisfying precision, this optimization procedure will be terminated. Otherwise, the design space will be decomposed into two or more subspaces. Then, the optimization will be carried on the approximation of these subspaces. If the subspace has no promise to get better optimization result than the optimum reached by other subspaces, the subspace will be discarded. If the subspace approximation precision has reached a satisfying precision, this subspace will not be decomposed into smaller subspace. If the subspace has not reached a satisfying precision and has promise to get better optima, this subspace will be decomposed into smaller subspaces. The calculation time of this process is related to the numbers of design variables and design space. Function optimization examples show that this optimization algorithm has good performance on calculation time and global optima.]]></description>
<pubDate>2012/8/28 11:51:54</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LUO Wencai,HUANG Yiyong,YANG Weiwei and LIU Changqing]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LUO Wencai,HUANG Yiyong,YANG Weiwei and LIU Changqing</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201105008]]></guid><cfi:id>507</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Research on the Influence of Rarefaction Wave to the Experimental Section in Blast Shock Tube]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201104001]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The influence of rarefaction wave on the experimental section in blast shock tube with different isolator lengths was simulated. To simulate the incident wave at the entrance of experimental section exactly and efficiently, a new method which couples 1D and 3D computational programs was adopted, and small scale explosion was utilized to simulate actual overpressure waveforms in 1D computation according to blast similarity rule. The computation results demonstrate the following features: alteration of isolator length L does not affect the peak overpressure; when L is less than or equal to 20m, influence of rarefaction wave will reduce the impact time and impulse of overpressure in experimental section; while L is larger than or equal to 30m, the rarefaction wave doesn't affect these two parameters in experimental section.]]></description>
<pubDate>2012/8/28 10:29:47</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[XU Chunguang<sup>1</sup>,BAI Xiaozheng<sup>2</sup>,LIU Yu<sup>1</sup> and LIU Jun<sup>1</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>XU Chunguang<sup>1</sup>,BAI Xiaozheng<sup>2</sup>,LIU Yu<sup>1</sup> and LIU Jun<sup>1</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201104001]]></guid><cfi:id>506</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Point Return Trajectory Characteristics Analysis for aLunar Spacecraft]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201104002]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The point return orbit characteristics for a vehicle from a lunar mission were studied, and how the landing point and reentry point
 vary was focused upon. Firstly, analysis of some characteristic points was presented, and lunar antipode, reentry point and perigee were included. Then the stabilization property of the latitude and velocity at reentry point was achieved. Furthermore, based on the characteristics of the foregoing three points, approximate method for the theoretical relation of landing point and reentry point was proposed. In addition, relation of lighting condition at landing point and lunar return window was analyzed by using lunar phase law, and the basic conclusions 
was attained qualitatively. Finally, the orbit simulation was established with double two-body model, which shows the feasibility of this theoretical model in predicting the lunar point return orbit.]]></description>
<pubDate>2012/8/28 10:29:47</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[SHEN Hongxin,LI Haiyang,PENG Qibo and DU Xin]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>SHEN Hongxin,LI Haiyang,PENG Qibo and DU Xin</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201104002]]></guid><cfi:id>505</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Simplification of a DF Chemical Laser Kinetic ModelBased on the Sensitivity Analysis]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201104003]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Based on the detailed DF chemical kinetic models of two different fuel systems, the relevant simplified chemical kinetic mechanisms were presented with the method of sensitivity analysis. It is found that considering the DF “cold reaction” pumping reactions, ignoring DF higher excited vibrational states and omitting the recombination-dissociation reactions have little effect on the total system. The energy transfer reactions in DF and DF deactivations by D, D<sub>2</sub> and HF exhibits strong sensitivity to the chemical kinetics. Compared with the detailed mechanism, the simplified mechanism describes the general DF combustion process effectively, and at the same time reduces the species, element reactions and computational costs to a great extent. Therefore it fits more with coupling with three-dimensional flowfield numerical simulation code or software.]]></description>
<pubDate>2012/8/28 10:29:47</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[SHAO Yan,ZHOU Jin,LIN Zhiyong and LAI Lin]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>SHAO Yan,ZHOU Jin,LIN Zhiyong and LAI Lin</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201104003]]></guid><cfi:id>504</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Multidisciplinary Semantic-oriented Data Management ofIntegrated Design for Vehicle]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201104004]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Focusing on the shortage of multidisciplinary data management systems of current integrated design environment, a dynamic integration and scheduling strategies of data was built, using a unified multidisciplinary semantic-oriented data management method on the basis of the analysis of characteristics of data in launch vehicle design process. The application in an integrated design environment of a solid rocket vehicle proves that the multidisciplinary semantic-oriented method separates data dealing from processing dealing, and simplifies the data description and access. Consequently, the flexibility, expansibility and versatility of vehicle integration design environment are enhanced.]]></description>
<pubDate>2012/8/28 10:29:47</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[XIAO Fei<sup>1,2</sup>,WANG Donghui<sup>1</sup>,CHEN Min<sup>1</sup> and ZHANG Weihua<sup>1</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>XIAO Fei<sup>1,2</sup>,WANG Donghui<sup>1</sup>,CHEN Min<sup>1</sup> and ZHANG Weihua<sup>1</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201104004]]></guid><cfi:id>503</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Study on Optimal Control for Halo Orbits Formation Reconfiguration]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201104005]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Changeable measurement baseline and diversity of space configuration are advantages of spacecraft formation implementing deep-space exploration mission. They are closely related to the reconfiguration capability of spacecraft formation. Aimed at the issue of optimal control for Halo orbits formation reconfiguration, this study firstly analyzed the configuration characteristics of Halo orbits formation, then the Hamiltonian equation of optimal control for Halo orbits formation reconfiguration were deduced. Iterative method for solving the Hamiltonian equation was built based on the first generating function. Simulation of optimal control for Halo orbits formation reconfiguration in the Earth-Moon system was carried out, and the validity of this iterative method was verified. Simulation results show that sun perturbation has huge influence
 on the fuel consumption of optimal control during the process of Halo orbits formation reconfiguration, and the fuel consumption can be reduced by selecting the reconfiguration times correctly.]]></description>
<pubDate>2012/8/28 0:00:00</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[ZHANG Yuedong<sup>1</sup>,Meng Yunhe<sup>1</sup>,Gui Chen<sup>2</sup> and DAI Jinhai<sup>1</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>ZHANG Yuedong<sup>1</sup>,Meng Yunhe<sup>1</sup>,Gui Chen<sup>2</sup> and DAI Jinhai<sup>1</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201104005]]></guid><cfi:id>502</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Numerical Study on a Counterflow Diffusion Flame for Hydrous Ethanol]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201104006]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The counterflow diffusion combustion of diluted ethanol in various containments was numerically analyzed in the purpose of getting 
a deep understanding of chemdynamics in a gas generator with low ethanol concentration. A virtual specie with the same thermodynamic and transport property as water but chemically inert was used to distinguish the interference between physical and chemical mechanism. Results reveal that as the concentration of ethanol decrease, the flame front, along with the disappearance of the second exothermic
 reaction region, tends towards the fuel side as a whole. The H<sub>2</sub>O will exert an inhibitory effect when the concentration of ethanol is reduced to the ultimate low value.]]></description>
<pubDate>2012/8/28 10:29:47</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[XI Wenxiong,LI Qinglian,KANG Zhongtao,ZHONG Zhan and WANG Zhenguo]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>XI Wenxiong,LI Qinglian,KANG Zhongtao,ZHONG Zhan and WANG Zhenguo</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201104006]]></guid><cfi:id>501</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Experimental Study of N<sub>2</sub>O/C<sub>7</sub>H<sub>8</sub> Mono-injector Gas Generator]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201104007]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In order to carry out ignition experiment on combustion-driven mixing gasdynamic CO<sub>2</sub> laser based on N<sub>2</sub>O/C<sub>7</sub>H<sub>8</sub>, a liquid N<sub>2</sub>O supply system and a N<sub>2</sub>O/C<sub>7</sub>H<sub>8</sub> mono-injector gas generator were designed. The liquid N<sub>2</sub>O supply system, ignition and combustion performances of N<sub>2</sub>O/C<sub>7</sub>H<sub>8</sub> were studied. Experimental results indicate that N<sub>2</sub>O can be supplied in liquid state by the designed liquid N<sub>2</sub>O supply system; ignition can be realized under two operating modes(excess oxidizer coefficient is 0.3 or 0.4) in designed time sequence and the combustor pressure is smooth. In addition, with the increase of excess oxidizer coefficient, combustion efficiency improves obviously.]]></description>
<pubDate>2012/8/28 10:29:47</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[ZHAI Xiaofei,ZHOU Jin and LAI Lin]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>ZHAI Xiaofei,ZHOU Jin and LAI Lin</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201104007]]></guid><cfi:id>500</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Design Research of Scramjet Inlet Based on the Optimization of Restarting Characteristics]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201104008]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The numerical study of hypersonic inlet flow with different inner compression surface was carried out, aimed at exploring the influence of horizontal angle of lower inlet surface on inlet performance specially restarting characteristics. The result shows that the reduction of surface horizontal angle on the tail of separation bubble will improve the performance of unstart flow and decrease the restart Mach number, with the disadvantage of increasing length of inner compression surface and reducing the performance of start flow. To optimize the synthetic performance of inlet, a new design of inner compression lower surface composed of the concave surface in the front and the straight
 surface with small horizontal angle in the rear was proposed. Compared with the prototype, the performance of start flow drop lightly under the same length for new inlet, but the restart Mach number of latter reduce from 9.4 to 8.]]></description>
<pubDate>2012/8/28 10:29:47</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[YOU Jin,XIA Zhixun,LIU Bin and WANG Dengpan]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>YOU Jin,XIA Zhixun,LIU Bin and WANG Dengpan</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201104008]]></guid><cfi:id>499</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Dynamic Stability Analysis of Supercavitating Double Shells]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201104009]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[A finite element model for supercavitating underwater vehicles was developed and the dynamic stability of supercavitating double shells was investigated to obtain the instability maps for varying vehicle's velocity considering the time-dependent properties of the longitudinal loads. The computational results indicate that with the increment of the thickness of the annular plates linking between inner and outer shells or the number and dimension of the circumferential stiffeners, the frequencies corresponding to dynamic instability decline and the extension of the regions of dynamic instability is reduced lightly, while the frequencies corresponding to dynamic instability ascend and the dynamic stability is enhanced remarkably with the space between inner and outer shells decreased or the number and dimension of the longitudinal stiffeners
 increased.]]></description>
<pubDate>2012/8/28 10:29:47</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[MA Zhenyu,HU Fan,CHEN Guangnan and ZHANG Weihua]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>MA Zhenyu,HU Fan,CHEN Guangnan and ZHANG Weihua</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201104009]]></guid><cfi:id>498</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[A Polynomial Approximation Algorithm for Free-Fight Trajectory Estimation under the Early Warning of LEO Satellite]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201104010]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The free-fight trajectory estimation by a single LEO satellite plays a key role in the space-based early warning system. An actual measurement function was established, and a polynomial approximation algorithm was proposed to reduce the computational amount of the batch algorithm of maximum-likelihood estimation (MLE). The approximate polynomial of the measurement function was evaluated at some deterministic instants to form pseudo measurement data. The raw measurement data were replaced by the pseudo ones to estimate the trajectory. The simulation results show that this new algorithm greatly reduces the computational amount, and can achieve the same accuracy performance as MLE.]]></description>
<pubDate>2012/8/28 10:29:47</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LI Dong<sup>1</sup>,YI Dongyun<sup>1</sup>,CHEN Hongwei<sup>2</sup> and ZHOU Wei<sup>3</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LI Dong<sup>1</sup>,YI Dongyun<sup>1</sup>,CHEN Hongwei<sup>2</sup> and ZHOU Wei<sup>3</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201104010]]></guid><cfi:id>497</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Autonomously Updated Broadcast Ephemeris Algorithm]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201103001]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The navigation constellation's autonomous navigation requires the autonomously updating of the broadcast ephemeris. In view of the limited   data-processing ability of the satellite, the forgetting factor recursive least-squares algorithm was introduced to improve the data-processing efficiency. Considering that the navigation satellite's orbit eccentricity is equal to zero approximately, it would result in the singularity of the normal matrix in the process of fitting. The new broadcast ephemeris parameters fitting algorithm was developed and the partial derivative matrix of satellite position vector with respect to modified parameter was deduced based on the non-singular transformation. Finally, the rationality of formulas and algorithm are validated by simulation.]]></description>
<pubDate>2012/9/13 9:40:50</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[CHEN Zhonggui,LIU Guangming,LIAO Ying and WEN Yuanlan]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>CHEN Zhonggui,LIU Guangming,LIAO Ying and WEN Yuanlan</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201103001]]></guid><cfi:id>496</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Multi-objective Optimization of Multi-impulse RendezvousTrajectory for Exploring Asteroids]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201103002]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The current studies on optimal rendezvous trajectories for exploring asteroids always concentrate on the fuel-optimal two-impulse rendezvous, while the aim of this paper is aimed to investigate the multi-objective optimization problem of multiple-impulse rendezvous for exploring asteroids. A multiple-impulse rendezvous optimization model using Lambert algorithm for exploring asteroids including earth departure and heliocentric transfer phases was established, which utilized minimum-fuel cost and minimum-time transfer as two objective functions. The    NSGA-II algorithm, a very representative multi-objective evolutionary algorithm, was employed to obtain the Pareto solution set. The effectiveness of the proposed optimization model and algorithm was testified by solving two asteroids mission design problems. The results show that the proposed method can effectively and efficiently demonstrate the relations among the mission characteristic parameters such as launch time, transfer time and total fuel cost, and analyze the influences of different impulse numbers, and also compare and evaluate different exploration missions. The proposed method has good application value for preliminary mission design for asteroid exploration.]]></description>
<pubDate>2012/9/13 9:40:50</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LI Jiutian,LUO Yazhong and TANG Guojin]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LI Jiutian,LUO Yazhong and TANG Guojin</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201103002]]></guid><cfi:id>495</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Effects of Configuration Parameters on CondensationField of Annular Vapour Ejector]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201103003]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The theoretical model for wet steam condensation flow was established. Furthermore, numerical simulation results with wet steam condensation flow model were coincident to the experimental data of C.A.Moses, which validated the credibility and accuracy of the model. Then, numerical simulation on condensation flow process was carried out under different configuration parameters. The results show that appropriately reducing the convergence ratio ?, area ratio and increasing the ι/d of secondary throat can increase the total pressure recovery coefficient，which improves the ejector performance.]]></description>
<pubDate>2012/9/13 9:40:50</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[ZHANG Minqin<sup>1</sup>,HU Xiaoping<sup>2</sup> and LIU Zejun<sup>2</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>ZHANG Minqin<sup>1</sup>,HU Xiaoping<sup>2</sup> and LIU Zejun<sup>2</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201103003]]></guid><cfi:id>494</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[The Aerodynamic and Structural Research of Mach6 Hypersonic Quiet Wind Tunnel]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201103004]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[First, the importance of developing hypersonic quiet tunnel facility and techniques was pointed out, and the basic characteristics of quiet tunnel were briefly discussed. Second, according to foreign and domestic experience and research results of developing quiet tunnel, the project about aerodynamic and structural research of mach 6 Hypersonic Quiet Wind Tunnel was presented. Furthermore, the design details of valves, settling chamber and slot exhaust of nozzle were proposed. Finally, M6HQWT design Mach number is 6.0, nozzle outlet diameter 120mm, T<sub>0</sub>500K,P<sub>0</sub>1-5MPa and operation duration 20-30s. M6HQWT is the first hypersonic quiet wind tunnel in China, and can be used for experimental teaching and basic scientific research.]]></description>
<pubDate>2012/9/13 9:40:50</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[ZHOU Yongwei,YI Shihe,CHEN Zhi,LU Xiaoge and GE yong]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>ZHOU Yongwei,YI Shihe,CHEN Zhi,LU Xiaoge and GE yong</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201103004]]></guid><cfi:id>493</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Attitude Control of Low-orbit Micro satellite]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201103005]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[A new scheme of attitude control with active magnetic torque and aerodynamic stabilization torque was proposed for low-orbit micro-satellite (orbit altitude lower than 500km), in order to take full advantage of environmental torque. Simulation results show that the characteristic distance of satellite d<sub>cc</sub> is the linchpin which influences the attitude control scheme. Suitable magnitude of d<sub>cc</sub> should be chosen in order to meet the request of satellite attitude control system. All this shows that the satellite structure proposed in the current study has the potentiality of being used for experimental teaching and research.]]></description>
<pubDate>2012/9/13 9:40:50</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[WANG Peng,ZHENG Wei,ZHANG Hongbo and WU Jie]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>WANG Peng,ZHENG Wei,ZHANG Hongbo and WU Jie</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201103005]]></guid><cfi:id>492</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Interfering Factors on Inlet Working Processin the Solid Rocket Ramjet]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201103006]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The working process of inlet under the condition of different given influencing factors in the inlet/combustor/nozzle integrated flow field was discussed. The effect of fluctuation of nozzle diameter on the inlet was investigated. We also explored the effect of time and space fluctuation of inlet exit pressure on the inlet. The operating characteristics of inlet with different interfering factors were achieved. The result showed that time fluctuation of inlet exit pressure can bring the non-uniform distribution of inlet exit pressure. The response time of space fluctuation was longer than the that of time fluctuation. The recirculation zone at the diffusers moved upward gradually when the nozzle diameter was reduced.]]></description>
<pubDate>2012/9/13 9:40:50</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[ZHAO Xiangheng,XIA Zhixun,HU Jianxin,WANG Dequan,FANG Chuanbo and YOU Jin]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>ZHAO Xiangheng,XIA Zhixun,HU Jianxin,WANG Dequan,FANG Chuanbo and YOU Jin</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201103006]]></guid><cfi:id>491</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Vector Modeling and Stability Analysis of a Near-spaceEarth Observation Platform]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201103007]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[A vectored mathematical model and stability of a near-space earth observation platform are presented in this paper. First, the reference frames and motion parameters of the platform was defined. Then, a nonlinear six degrees of freedom mathematical model in vector form of the platform was derived based on Newton-Euler principle. Finally, stability of the platform was analyzed by means of Lyapunov stability theory. The results show that the platform is asymptotic stability for the equilibrium. The longitudinal motion and lateral motion of the platform under initial disturbances are both composed of two non-periodic attenuation modes and an oscillation attenuation mode. The fast attenuation mode is related to the angular velocity motion and reflects the process of moments balancing, while the slow attenuation mode is related to the linear velocity and reflects the process of forces balancing.]]></description>
<pubDate>2012/9/13 9:40:50</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[YANG Yueneng,ZHENG Wei,WU Jie and ZOU Dongsheng]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>YANG Yueneng,ZHENG Wei,WU Jie and ZOU Dongsheng</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201103007]]></guid><cfi:id>490</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Coordinated Robust Control of Space Electromagnetic Docking]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201103008]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Space electromagnetic docking is characterized by such advantages as no propellant consuming, continuous reversible ability and no plume contaminations, thus ensuring a broad prospect of application. The control difficulties of space electromagnetic docking lie in nonlinearity, uncertainty and coupling, etc. Given these, this paper synthesized LESO, feedback linearization and robust H<sub>∞</sub>control technology, designed a coordinated robust control and verified the performance and robust ability of the proposed control scheme through simulation. Simulation results show that the proposed control scheme is capable of observing all states, improving the robust ability to model error and external disturbance and performing good tracking control functions.]]></description>
<pubDate>2012/9/13 9:40:51</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[ZHANG Yuanwen,YANG Leping,ZHU Yanwei and REN Xianhai]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>ZHANG Yuanwen,YANG Leping,ZHU Yanwei and REN Xianhai</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201103008]]></guid><cfi:id>489</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[TT&C Scheduling Upper Bound Solution Algorithm Based onLagrangian Relaxation]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201103009]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The TT&C demand of TT&C Scheduling problem was analyzed and a model of TT&C Scheduling 0-1 integer programming was constructed. The model's facility constraints and satellite constraints were relaxed by lagrangian relaxation method, and an upper bound of lagrangian dual problem by subgradient optimization algorithm was obtained. Finally, two examples were tested. The results demonstrate the validity of upper bound obtained by subgradient optimization algorithm.]]></description>
<pubDate>2012/9/13 9:40:51</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[KANG Ning and WU Xiaoyue]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>KANG Ning and WU Xiaoyue</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201103009]]></guid><cfi:id>488</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Three Dimensional Large Eddy Simulation of SupersonicCombustion Flowfield with  Strut]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201101001]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Flamelet model and hybrid LES/RANS method were used to simulate SCRAMJET with strut for the Chemical Propulsion of the German Aerospace Center (DLR). The effect of reaction on turbulence was discussed, and comparison between 2D and 3D simulation were presented. The results show the following indication: (1) Mixing is controlled by large eddy scales in nonreacting flow,and the shear layer has three effects obviously； In addition, the combination and pairing of large eddy scales can be seen in 2D simulation, while stretching, distorting and breaking up can be seen in 3D simulation；(2) In reacting case, jet penetration decreases and recirculation zone becomes larger, while, owing to heat release, large eddy scales turn up and saturation appears late. (3) Numerical shadow picture displays good agreement with experimental shadow photograph, while velocity and temperature measurements are consistent with experimental data qualitatively and quantitatively, but 3D model is superior to 2D model in result accuracy.]]></description>
<pubDate>2012/8/29 10:50:38</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[FAN Zhouqin,SUN Mingbo and LIU Weidong]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>FAN Zhouqin,SUN Mingbo and LIU Weidong</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201101001]]></guid><cfi:id>487</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Fitting Starlight Atmosphere Refraction Model on Line UsingSatellite Navigation Data]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201101002]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The autonomous navigation system based on starlight atmosphere refraction has simple structure and low cost. Using the system, the spacecraft can get high-precision navigation data. But the measurement model has some imprecise atmospheric parameter, which reduces the navigation precision and reliability seriously. The above effects can be avoided by nervous network fitting starlight atmosphere refraction model on line, using satellite navigation data, when the spacecraft is at low orbit. This method can improve the navigation precision based on starlight refraction. Through simulation, the characteristics of the starlight refraction model and the fitting method were researched, and the precision analysis of the fitting models were also made.]]></description>
<pubDate>2012/8/29 10:50:38</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[WEN Yongzhi and WU Jie]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>WEN Yongzhi and WU Jie</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201101002]]></guid><cfi:id>486</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Shape Optimization of Wheel Shape Grain Based onParameterized Modeling]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201101003]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In the process of SRM (Solid Rocket Motor) grain configuration design, high loading fraction always gives rise to high stress and train in the grain, and the structure integrity of grain turns hard to satisfy. To solve this problem, the integration of GA (Genetic Algorithm) and parameterized modeling method was applied to shape the optimization of the wheel shape grain. Parameterized finite element analysis model was constructed by PCL (Patran Command Language), the secondary development tool of MSC.Patran. Based on the model, the finite element mesh could be established and the maximum strain and loading fraction of grain could be exported when the geometric parameters were given.This made it convenient for GA to call, as a function. A shape optimization of a high loading fraction wheel shape grain was carried out, and the optimal grain was found. The maximum strain of the optimal grain, under low temperature load,was 30% less than the initial grain's. Meanwhile, the loading fraction remained the same. The results show that the method presented is feasible and available,and it can be applied to SRM grain configuration design of all sorts.]]></description>
<pubDate>2012/8/29 10:50:38</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LI Lei,TANG Guojin,DUAN Jingbo and SHEN Zhibin]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LI Lei,TANG Guojin,DUAN Jingbo and SHEN Zhibin</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201101003]]></guid><cfi:id>485</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Numerical Simulation of Three-dimension Flow Field in an Air-heater]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201101004]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[An air-heater was designed for scramjet ground test. The internal flow field in the air-heater was investigated and the results were compared with the test data. The results show that the air-heater basically corresponds with the structure project and performance, the temperature of faceplate is reduced as a result of the air flow from injector-inlet, and the inner surface of the combustion chamber is protected by air flow from chamber-inlet. The results will be helpful for the optimization of the air-heater design.]]></description>
<pubDate>2012/8/29 10:50:38</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[SHEN Chibing,LIU Youpeng and WU Haiyan]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>SHEN Chibing,LIU Youpeng and WU Haiyan</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201101004]]></guid><cfi:id>484</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Flight Performance Analysis of Variable Flow Ducted Rocket]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201101005]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Based on ducted rocket operating principle, mathematical working model of air inlet, gas generator and secondary chamber was built.
 The altitude characteristics and velocity characteristics of variable flow ducted rocket were numerically studied. Increasing the flight mach or decreasing the flight altitude can not only help the engine work in a wide range of thrust, but also decrease the thrust coefficient. Decreasing the area of gas regulation valve can increase thrust and thrust coefficient]]></description>
<pubDate>2012/8/29 10:50:38</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[JIAO Jige,ZHANG Weihua,XIA Zhixun,HU Jianxin and MA Likun]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>JIAO Jige,ZHANG Weihua,XIA Zhixun,HU Jianxin and MA Likun</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201101005]]></guid><cfi:id>483</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Broadband Design of Ceramic Radome Material withSingle-layer Structure]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201101006]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Based on the requirement of broadband radome, by using the transmission line theory, the calculation method of transmission efficiency of single-layer structure was conducted when the frequency varied from 2GHz to 18GHz and the incidence angle changed from 0 to 40°,the dielectric properties were optimally designed. The results suggest that when the dielectric constant is no more than 3.0 and the loss angle tangent value is no more than 0.02, the transmission efficiency of single-layer structure material with the suitable  wall thickness is more than 60%. According to the design results, considering the mechanical and thermal properties, the hollow silica fiber reinforced BN-Si<sub>3</sub>N<sub>4</sub> matrix composites (SiO<sub>2f</sub>/BN-Si<sub>3</sub>N<sub>4</sub> composites) are selected as single-layer structure radome material. According to the dielectric properties of the composites (ε=2.8，tanδ=0.005), the structural parameter (thickness) was optimally designed, and the optimal wall thickness was 7mm. The broadband properties of SiO<sub>2f</sub>/BN-Si<sub>3</sub>N<sub>4</sub> single-layer structure radome material in agreement with the wall thickness requirement were tested. The results suggest that the transmission efficiency for single-layer structure radome material  is more than 60% when the frequency is 2～18 GHz.]]></description>
<pubDate>2012/8/29 10:50:38</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[ZOU Xiaorong<sup>1,2</sup>,ZHANG Changrui<sup>2</sup>,LI Bin<sup>2</sup>,MO Jinjun<sup>3</sup>,WANG Siqing<sup>2</sup> and CAO Feng<sup>2</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>ZOU Xiaorong<sup>1,2</sup>,ZHANG Changrui<sup>2</sup>,LI Bin<sup>2</sup>,MO Jinjun<sup>3</sup>,WANG Siqing<sup>2</sup> and CAO Feng<sup>2</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201101006]]></guid><cfi:id>482</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Multi-sensor Image Matching Based on Spatial Sub-area Congruency]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201101007]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[A novel multi-sensor image matching method based on spatial sub-area congruency is proposed. In this method, images were segmented into sub-areas with same size. The structure feature represented by matrix of surrounding similarity was obtained by calculating the similarity of intensity histogram of each pair of adjacent sub-areas, and was used to compute spatial sub-area congruency. Through employing optimized searching algorithm, the matching result was acquired. Experimental results show that the proposed method can match multi-sensor images stably and fast and outperforms conventional methods]]></description>
<pubDate>2012/8/29 10:50:39</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LI Zhuang,YANG Xia and LEI Zhihui]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LI Zhuang,YANG Xia and LEI Zhihui</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201101007]]></guid><cfi:id>481</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Numerical Analysis of Reaction Characteristics of Mg with Vapor Based on Diffusional and Chemical Dynamic Control]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201101008]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In order to numerically study the reaction characteristics of magnesium and vapor in broad temperature range, the reaction model based on diffusional and chemical dynamic control respectively was established. The diffusional control model considered the partial condensation of gaseous MgO on the surface of magnesium droplet. The chemical dynamic model of Mg/H<sub>2</sub>O reaction was based on the Arrhenius equation. The reaction rate of Mg/H<sub>2</sub>O at different conditions was studied numerically. The results show that the calculated results are consistent with the experimental results. The reaction rate is great at high temperature and concentration of vapor, but low at high pressure. The reaction rate of magnesium and vapor is controlled by different factors at different temperature region. The reaction rate is controlled by chemical dynamic below the critical transition temperature, but by diffusional dynamic above the critical transition temperature.]]></description>
<pubDate>2012/8/29 10:50:39</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[ZHOU Xing,ZHANG Wei,YANG Dong,BAO Tong and YAO Ruliang]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>ZHOU Xing,ZHANG Wei,YANG Dong,BAO Tong and YAO Ruliang</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201101008]]></guid><cfi:id>480</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Spacecraft attitude determination based on Euler angle 
measurement model]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201206014]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[For the multiplicative quaternion-error attitude determination approach, the attitude sensors for Euler angle measurements are studied. Two different methods were used to demonstrate that the measurement sensitivity matrix of Euler angle error with respect to error quaternion solved in many references is false. The correct measurement sensitivity matrix is presented and the reason for this mistake is analyzed in detail, and the numerical examples are given for the validation and verification of the conclusions.]]></description>
<pubDate>2013/1/11 4:19:30</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[ZHANG Lijun<sup>1</sup>,ZHANG Shifeng<sup>1</sup>,YANG Huabo<sup>1</sup> and QIAN Shan<sup>2</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>ZHANG Lijun<sup>1</sup>,ZHANG Shifeng<sup>1</sup>,YANG Huabo<sup>1</sup> and QIAN Shan<sup>2</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201206014]]></guid><cfi:id>479</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[The rapid engineering aero-heating calculation method 
for complex shaped hypersonic vehicles]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201206015]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Aimed for the question of computational efficiency during conceptual design stage, a rapid engineering aero-heating calculation method for complex shaped hypersonic vehicles is established. Firstly the pressure distribution along vehicle’s surface was calculated by modified Newtonian theory. Secondly, the streamline that passes through the target point was calculated with Newtonian steepest decent concept. Then by using the fitted function of high temperature gas parameters, reference enthalpy method and engineering calculation function of aero-heating, the heat current of target point was presented. Finally, the heat flux on the surfaces of blunted cone, lifting body and wave-rider vehicle was calculated The analysis result shows the method used in this paper is fit for complex figure, and can satisfy the aero-heating calculation during conceptual design stage in both efficiency and precision.]]></description>
<pubDate>2013/1/11 4:19:30</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LI Jianlin,TANG Qiangang,HUO Lin and CHENG Xinghua]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LI Jianlin,TANG Qiangang,HUO Lin and CHENG Xinghua</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201206015]]></guid><cfi:id>478</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Numerical simulation of gel propellant drop 
formation from capillary tube]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201206016]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Understanding drop formation of gel fuel is the first stage to conduct experimental investigation on combustion characteristics of single gel fuel droplet, and the formation of liquid drops at the end of a capillary tube is one of conventional methods. In order to investigate the formation of gel propellant drops at the end of a capillary tube, the Navier-Stokes equations were solved, and the VOF (volume of fluid) method is employed to track the gas/liquid interface during process of drop formation. The variation of dimensionless neck diameter DN/D0 and dimensionless drop height L/D0 with time was analyzed, which agreed with the existing experimental results and validated the numerical model. The results show that drop is not always at the steady state; there is high shear rate at the drop neck, leading to dynamic viscosity decreasing and drop pinch-off; then drop pinch-off, the part of conjoint drop, coalesces into drop rapidly, and high positive velocity appears; however, the part of conjoint capillary tube coalesces into gel propellant at the end of capillary tube rapidly, and the high negative velocity appears.]]></description>
<pubDate>2013/1/11 4:19:30</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LIU Zejun,WU Jianjun,HE Zhen and HU Xiaoping]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LIU Zejun,WU Jianjun,HE Zhen and HU Xiaoping</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201206016]]></guid><cfi:id>477</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Active collision avoidance maneuver strategy 
for on-orbit spacecraft]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201206017]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The active evasion strategy of spacecraft is discussed when the distance between spacecraft and target is relatively short. Firstly, the relative dynamic model is analyzed. The relative motion can be decomposed into two submotions, viz., the relative motion in the instantaneous rotation of the line of sight (IRPL) and the rotation of this plane. Secondly, the optimum evasion direction of the spacecraft is proposed, through the analysis of the relative motion in IRPL. Thirdly, the determination of this direction in the inertial space is discussed. Finally, the numerical simulation is conducted with different maneuver accelerations and different detective distance of the spacecraft. The effectiveness of the active evasion strategy is demonstrated with the simulation results.]]></description>
<pubDate>2013/1/11 4:19:30</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[YAO Dangnai and WANG Zhenguo]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>YAO Dangnai and WANG Zhenguo</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201206017]]></guid><cfi:id>476</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[A semi-qualitative fault isolation method based on analytical 
redundancy relations for spacecraft propulsion system]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201206018]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Based on time-varying characters of spacecraft propulsion system and stochastic properties, the semi-qualitative fault isolation method which combines the Z-test and Analytical Redundancy Relations (ARRs) has been proposed. Firstly, based on the insight of state spatial alternation, it is achievable to mining time-invariant structural characters space using ARRs for Spacecraft Propulsion System which is built on the Diagnostic Bond Graph, and by the tendency analysis of the residuals of ARRs, the time-invariant fault signature matrix with change direction can be established. Secondly, the Z-test for robust qualitative residual generation to established observed signature against infection from multi-uncertainty is used, and then faults are isolated by comparison of observed signature and fault signature. Through the analysis of isolation results of a spacecraft propulsion system, it shows that the method is valid for overcoming the challenges from establishing time-varying diagnostic criteria and the jamming from stochasticity not only in the system model, but also in the measurements, which improves the robustness in fault isolation.]]></description>
<pubDate>2013/1/11 4:19:30</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[PENG Xiaohui,YAN Zheng,LI Yanjun and WU Jianjun]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>PENG Xiaohui,YAN Zheng,LI Yanjun and WU Jianjun</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201206018]]></guid><cfi:id>475</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Parameters optimization algorithm for ring truss deployable antenna 
structures based on Kriging model]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201206019]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The solution efficiency for the traditional structure dynamic optimization process is relatively low. Based on a discussion of the parameters optimization for the ring truss deployable antenna structures, this research chose the sample points by design of experiment method in the variable parameter space. The response values of the first order natural frequency, total mass, and the maximum deformation with specific loading for the ring truss deployable antenna structures were obtained by the finite element method. The Kriging models, which were established by the relationship between the sample points and response values, were used to find the optimum solution with optimization algorithm. It is required that the optimum solution should satisfy all the constrained conditions. The results showed that the response surfaces of the first order natural frequency, total mass, and the maximum deformation with specific loading for the ring truss deployable antenna structures were nonlinear relationship with the design variable. The structure optimization method with the Kriging approximate model can be used to find the optimum structural parameters of the ring truss deployable antennas accurately.]]></description>
<pubDate>2013/1/11 4:19:30</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[HE Xingxing and LIAO Ying]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>HE Xingxing and LIAO Ying</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201206019]]></guid><cfi:id>474</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Trajectory optimization of planing supported supercavitating flight]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201206020]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Forces and dynamic equations of supercavitating vehicles were analyzed in detail in the paper; the mathematic model of the optimal diving trajectory was established in the vertical plane. Considering the time-delay effect during the expansion and contraction of supercavity, the Time Delay Gauss Pseudospectral Method(TDGPM) was introduced. Based on the information of discretized nodes, the TDGPM interpolated the real time cavity shape for each node and calculated the dynamic equations, which were used as constraints during the optimization process. Numerical solution of optimal diving trajectories and corresponding maneuvers were obtained. Results show that supercavitating vehicles without fins can achieve stable and maneuverable flight by applying proper cavitator control. Results also indicate the feasibility of TDGPM and its fast convergence.]]></description>
<pubDate>2013/1/11 4:19:30</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LIN Mingdong,YANG Xixiang,ZHANG Weihua,HU Fan and MA Zhenyu]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LIN Mingdong,YANG Xixiang,ZHANG Weihua,HU Fan and MA Zhenyu</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201206020]]></guid><cfi:id>473</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Designing method of supersonic nozzle with controllable contour]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201205001]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[A designing method of supersonic nozzle with controllable contour based on B-Spline curve and characteristic line algorithm is proposed. The contour of the nozzle was adjusted by assigning the distribution of Mach number on the nozzle’s axis. The reliability of the designing method was validated by numerical simulation, which shows that the outflow of the nozzle with high quality can be produced and the contour can be adjusted freely. The result also shows that the nozzle designed by the proposed method can produce better flow than the minimal length nozzle(MLN) with the same length.]]></description>
<pubDate>2012/11/5 8:48:02</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[ZHAO Yilong,ZHAO Yuxin,WANG Zhenguo and YI Shihe]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>ZHAO Yilong,ZHAO Yuxin,WANG Zhenguo and YI Shihe</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201205001]]></guid><cfi:id>472</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Robust attitude control of space electromagnetic docking]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201205002]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Space electromagnetic docking technology has perfect application for on-orbit servicing, but the electromagnetic and geomagnetic torques it brings create disturbances to the docking attitude. Also, the problems resulted from nonlinearity and coupling properties exist in the attitude controller design of space electromagnetic docking. The combined method of feedback linearization andH<sub>∞</sub>, extended state observer andH<sub>∞</sub>was proposed to design robust attitude controller for absolute/relative dynamics respectively, and the mentioned problems are better resolved. The advantages and shortages of the two control strategies are compared and researched, and the feasibility of designed controllers is verified by simulation. From theoretical research and simulation verification, it is right to put forward that the two control strategies are feasible and have better robust performance to model parameter change and outer disturbance, and the strategy of relative attitude control design is better for its preferably using measure information and no state estimator needs to be added.]]></description>
<pubDate>2012/11/5 8:48:02</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[ZHANG Yuanwen,YANG Leping,ZHU Yanwei and HUANG Huan]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>ZHANG Yuanwen,YANG Leping,ZHU Yanwei and HUANG Huan</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201205002]]></guid><cfi:id>471</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[The hardware-in-loop simulation system of X-ray-pulsars-based navigation



X ray pulsars based navigation]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201205003]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[A hardware-in-the-loop simulation system for X-ray pulsar navigation was built in order to do some research for the key technologies in X-ray pulsar navigation field. The system consists of an X-ray pulsar source simulation unit, an X-ray photon receive unit and a navigation estimate unit. The system can simulate X-ray pulsar with different intensities, periods and pulse profiles. The TOA of individual X-ray photon was recorded, and the pulse profile was reconstructed with these data. By comparing the measured pulse profile with the standard pulse profile of the X-ray pulsar source generator, the pulse TOA and the navigation estimation were calculated in the DSP chip. This system is proved effective in test some pulsar navigation algorithms, and can provide reference for the test of feasibility, dynamics and the project application for related X-ray pulsar navigation.]]></description>
<pubDate>2012/11/5 8:48:02</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LIU Li,ZHENG Wei,TANG Guojian and SUN Shouming]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LIU Li,ZHENG Wei,TANG Guojian and SUN Shouming</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201205003]]></guid><cfi:id>470</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Theory and experiment for vibration analysis of liquid-filled tank with internal pressure]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201205004]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[A theoretical and experimental investigation of the vibration characteristics of fluid-filled tank with internal pressure is presented. The dynamic equations of vibration are based on the elastic mechanics and velocity potential theory. The form related to the difference of pressure inside and outside was given by analysis of its effects on the tank. Also the form related to the solid-fluid interaction was given by analysis of its effects. The classic boundary-value approach was used here to calculate the natural frequencies of the tank. A modal experiment about vibration characteristics of fluid-filled tank with internal pressure was conducted, and the frequencies were measured. Results of theoretical calculation agree with the experimental data, which indicates that the frequencies of the tank decrease when filled with liquid, but they increases with internal pressure, compared with that of the empty tank. Further analysis of the results shows the effects of factors, such as the wave number, internal pressure, fluid density, structural geometric parameters and flexural rigidity of the tank on the dynamical behaviors.]]></description>
<pubDate>2012/11/5 8:48:02</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LEI Yongjun,YANG Zhen,WANG Chenglong,SONG Xiancun and LI Daokui]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LEI Yongjun,YANG Zhen,WANG Chenglong,SONG Xiancun and LI Daokui</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201205004]]></guid><cfi:id>469</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Optimal guidance law based on hit point forecast 
for maneuvering target]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201205005]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[A method of hit point forecasting based on “current” statistical model is proposed for maneuvering target attacked by missiles. The method detects the target maneuvering in real time. In addition, it forecasts the hit point. Based on the forecasting, the optimal guidance law for maneuvering target attacking has been studied, while the analytic solution has been obtained. Based on the proposed method, assumption of target maneuvering model is needless. The results of simulations of several hypothetical scenes have proved that the method is effective.]]></description>
<pubDate>2012/11/5 8:48:02</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[WAN Yujun,LIU Luhua,CHEN Kejun and WU Jie]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>WAN Yujun,LIU Luhua,CHEN Kejun and WU Jie</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201205005]]></guid><cfi:id>468</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Fuzzy variable structure attitude control for a near-space airship]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201205006]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The near-space airship provides a unique and promising platform for telecommunication, broadcasting relays, surveillance, and scientific exploration. A key control technical challenge for a near-space airship is station keeping, the ability to remain fixed over a geo-location. A fuzzy variable structure control approach for an airship is proposed. First, problem formulation of an airship’s attitude control was derived. Second, the attitude control system was designed by using the variable structure control theory, and a fuzzy system was used to turn the control gains for better performance of eliminating chattering. Finally, simulation results demonstrate the effectiveness and robustness of the proposed control approach in the presence of parameter uncertainties.]]></description>
<pubDate>2012/11/5 8:48:02</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[YANG Yueneng,WU Jie and ZHENG Wei]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>YANG Yueneng,WU Jie and ZHENG Wei</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201205006]]></guid><cfi:id>467</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[The threat assessment method of optics imaging reconnaissance satellite]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201205007]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The ground forces have to face more and more threat from the space in future operations. The primary threat is coming from reconnaissance satellites. The threat assessment method of optics imaging reconnaissance satellite was studied. The methods to evaluate image quality of remote sensing satellites and the influence factors of image quality were discussed. The ground target discrimination probability model of optics image reconnaissance satellites was formulated, and amended by influence coefficients of illumination, weather and contrast. Taking into account military task, the expressions of threat degree were formulated when target size was given. The threat degree was then divided into several rankings according to the target size to support the military operations decision, and the evaluation method of threat ranking of optics image reconnaissance satellites was presented. Finally, the method was applied to threat evaluation of an optics image reconnaissance satellite, and the result was given.]]></description>
<pubDate>2012/11/5 8:48:02</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[ZHANG Yi,LIANG Yangang,CHEN Lei and TANG Guojin]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>ZHANG Yi,LIANG Yangang,CHEN Lei and TANG Guojin</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201205007]]></guid><cfi:id>466</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Aeroengine measurable parameters estimation using adaptive Kalman filter algorithm]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201204001]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Aeroengine onboard adaptive model can be built by estimating the biases of measurable parameters, so the CA (constant acceleration) model was introduced to establish the measurable variables state-space equations and observation equations, and adaptive Kalman filter algorithm was employed to estimate the measurable variables directly. The bias of measurable variables can be obtained by subtracting standard model computing values from the estimated result of measurable variables. When using the standard Kalman filter algorithm to estimate the measurable parameters, the results will offset prominently because of the great system state-space model error. The principle of standard Kalman filter and the impact of model error to the filter estimate results were analyzed, and the technology of dynamically adjusting the weight of state prediction in the filter estimate results was introduced, then the single factor adaptive Kalman filter estimation principle and the recursion formula were presented, which was aimed to make the estimation more accurate. In order to reduce calculation cost, the sequence filter was applied separately to process different measured parameters. The algorithm and system model were verified using the simulated data. The calculation results show that the designed filter can converge rapidly, and the computing speed is satisfied. The estimate results are better than the standard filter’s. So the adaptive filter algorithm has better estimation precision and have some engineering value. ]]></description>
<pubDate>2012/9/12 9:00:48</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LIAO Ying<sup>1</sup>,YIN Dawei<sup>2</sup>,ZHENG Yuxin<sup>1</sup> and MEN Lu<sup>3</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LIAO Ying<sup>1</sup>,YIN Dawei<sup>2</sup>,ZHENG Yuxin<sup>1</sup> and MEN Lu<sup>3</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201204001]]></guid><cfi:id>465</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[A numerical study of combustion and heat transfer  in small thrust liquid rocket engine]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201204003]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[By introducing VOF model to simulate the cooling liquid film in small thrust liquid rocket engine, numerical method was performed to calculate and evaluate the effects of the expansion size on combustion efficiency and heat transfer in the chamber. Comparison shows the calculation is reasonable. It has shown that as the dimensionless expansion height H<sup>*</sup>increases from 0.111 to 0.222, combustion efficiency and specific impulse increase by 0.35 % and 0.5s. However, the dimensionless expansion length L<sup>*</sup>plays a less significant role in the process. As it increases from 1.389 to 1.944, combustion efficiency and specific impulse decrease by 0.11 % and 0.3s respectively. It is evident that the heat transfer characteristics of thrust chamber keep stable in the variation of H<sup>*</sup>or L<sup>*</sup>. This shows in expansion thrust chamber, the main reason for combustion efficiency loss should be that gaseous MMH adjacent side wall cannot mix with gaseous oxidant efficiently. ]]></description>
<pubDate>2012/9/12 9:00:48</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LIN Qingguo<sup>1,2</sup> and ZHOU Jin<sup>1</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LIN Qingguo<sup>1,2</sup> and ZHOU Jin<sup>1</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201204003]]></guid><cfi:id>464</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[A study of propellant flow in the vane-type surface tension tank based on interior corner flow]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201204004]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The flow and distribution of propellant in the vane-type surface tension tank in microgravity condition was studied. The rewetting process of propellant in tank was calculated by numerical simulation using VOF method, and the liquid management capability of the tank and PMD was tested. The interior corner flow of propellant along the PMD was investigated by analytical solutions, and the length of the meniscus in the tank was calculated, and the results were compared with the numerical simulation results. Inevitably, errors were noticed between numerical simulation and analytical solution due to the complication of the model of spherical tank with PMD, but they were in accordance with the tendency of the flow. The present research can provide useful reference for the study of interior corner flow.]]></description>
<pubDate>2012/9/12 9:00:48</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LI Jinghao<sup>1,2</sup>,CHEN Xiaoqian<sup>1</sup> and HUANG Yiyong<sup>1</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LI Jinghao<sup>1,2</sup>,CHEN Xiaoqian<sup>1</sup> and HUANG Yiyong<sup>1</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201204004]]></guid><cfi:id>463</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Numerical simulation on the aerodynamic performance of hypersonic glide vehicle]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201204005]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The waverider is considered as an important candidate for the configuration of hypersonic glide vehicle (HGV) in terms of its high lift-to-drag ratio. Due to the severe aerodynamic heating, the sharp leading edge of waverider need be blunted, and the flow characteristics and the aerodynamic performance along the trajectory will change. In the current research, the flow characteristic of a HGV was studied based on a reference trajectory, and a numerical simulation was carried out to evaluate the performance of HGV with a blunt leading edge under a typical condition. The result indicates that the flow near the stagnation point exhibits three-dimensionality which cannot be approximated as a flow around a sphere or cylinder; the heat flux can be reduced and the aerodynamic performance of HGV may decrease as well when the leading edge is blunted: under the condition of 2 cm radii, the lift-to-drag ratio reduces by 12.34%, and different thermal protection methods can be used in different places of HGV.]]></description>
<pubDate>2012/9/12 9:00:48</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LIU Jianxia,HOU Zhongxi,CHEN Xiaoqing and GAO Xianzhong]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LIU Jianxia,HOU Zhongxi,CHEN Xiaoqing and GAO Xianzhong</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201204005]]></guid><cfi:id>462</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Modular modeling of spacecraft propulsion system]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201204006]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In order to investigate the system dynamics of spacecraft propulsion system with complex pressurization pipelines and propellant feed pipelines, the Unified Propulsion System simulator (UPSSim) was developed, which consists of a modular and extensible framework based on AMESim software. The pressurant pipelines were separated into several nodes, with each node using lumped parameter model; while the propellant feed pipelines used distributed parameter model. Heat transfer between components and environment was also taken into account. Simulation of a certain UPS during GEO insertion shows that the UPSSim can obtain the parameter variations accurately, and the results are in good agreement with design parameters and measurements. Simulation result indicates that the method proposed is sufficient for the modeling of complex pipelines and has good application prospect for spacecraft propulsion system dynamic simulation. ]]></description>
<pubDate>2012/9/12 9:00:48</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[YAN Zheng,LIU Zejun,CHENG Yuqiang and WU Jianjun]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>YAN Zheng,LIU Zejun,CHENG Yuqiang and WU Jianjun</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201204006]]></guid><cfi:id>461</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Simulation reappearance of a certain type of gas generator’s failure]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201204007]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[To meet the needs of failure reappearance of a certain rocket launching, the present research studied the conceivable failure condition by the method of numerical simulation. Firstly, the conceivable failure reasons were analyzed based on the failure phenomenon and the measure data from rocket. Then, the processes of the atomization and the combustion were numerically modeled and simulated, which was based on the performance of the gas generator. Next, the possible failure conditions were simulated one by one, and the results were compared with the limited data from the rocket. The conclusions are as follows: the numerical model proposed can simulate the rocket launching failure very well; the gas generator involved has some design objection, and needs  to be optimized in design; the askew turbulent flow annulus is the most possible failure of this rocket launching.]]></description>
<pubDate>2012/9/12 9:00:48</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[CHENG Lin<sup>1,2</sup> and TANG Guojian<sup>1</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>CHENG Lin<sup>1,2</sup> and TANG Guojian<sup>1</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201204007]]></guid><cfi:id>460</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Dynamic analysis of a large scale satellite structure with the liquid propellant consuming]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201204008]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[A simplified ‘Spring-Mass’ dynamic model and dynamic analysis were performed to obtain the influence of propellant consuming on the dynamic properties of a large scale satellite structure. Then the finite element modeling and analysis methods, including the beam modeling method, added with the mass method, the ‘RBE3-Mass’ modeling method and the virtual mass method, were given based on MSC.PATRAN/NASTRAN. In the end, the satellite finite element model was established and the dynamic analysis was executed. The analysis results indicate that: (1) the frequencies of main mode shapes will raise with the propellant consuming, while those of local shapes will not change ; (2)The frequency and magnitude of response will raise with the propellant consuming.]]></description>
<pubDate>2012/9/12 9:00:49</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[WU Xinfeng,LEI Yongjun and LI Daokui]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>WU Xinfeng,LEI Yongjun and LI Daokui</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201204008]]></guid><cfi:id>459</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Analysis of liquid and gaseous oxygen influence on the combustion flow field of air heater]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201204009]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The evaluation index, such as spray combustion, gas mixing and nozzle non-uniformity of air heater based on the combustor of liquid rocket engine, was studied with numerical simulation. The difference between the injectors with ethanol/liquid oxygen/air and the injectors with ethanol/gaseous oxygen/air in the combustion flow field was discussed and analyzed. Two cases were designed by changing the characteristic length of combustor, and the performance of air heaters were investigated by numerical simulation. The results show that, the flame structure is affected obviously by the phase of oxygen. The length of flame with liquid oxygen is larger than that of gaseous oxygen. More hot gas fills in the recirculation zone in the forepart of combustor with gaseous oxygen case, which increases the gas temperature near the faceplate, and worsens the thermal environment on the faceplate. The high quality flow field on the nozzle exit is obtained with the designed air heater. The characteristic length of air heater with gaseous oxygen is at least a quarter less than that of air heater with liquid oxygen to keep the good uniformity of nozzle exit.]]></description>
<pubDate>2012/9/12 9:00:49</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[FENG Junhong,SHEN Chibing and ZHAO Fang]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>FENG Junhong,SHEN Chibing and ZHAO Fang</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201204009]]></guid><cfi:id>458</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Research of attitude control for fast maneuvers of responsive spacecraft]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201204010]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The control process for the fast maneuvers of the responsive spacecraft was taken as the research object, and the rapid decoupling of the attitude control problem was investigated. A comprehensive control strategy which integrates time optimal control and tilt switch curve control was proposed based on the decision tree theory. Furthermore, the control time was taken as the cost function, the three-channel time optimal control strategy was obtained. Compared with other methods, the control time of the proposed strategy is reduced by nearly 10 seconds, and the control precision meets the design requirements. Additionally, control results were compared in case of different control cycles for the controller, and the instructional conclusions were provided for selecting and designing of the control cycle.]]></description>
<pubDate>2012/9/12 9:00:49</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[HUANG Wenbo<sup>1,2</sup>,JIANG Zhenyu<sup>1</sup>,ZHANG Weihua<sup>1</sup> and CAI Yequan<sup>2</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>HUANG Wenbo<sup>1,2</sup>,JIANG Zhenyu<sup>1</sup>,ZHANG Weihua<sup>1</sup> and CAI Yequan<sup>2</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201204010]]></guid><cfi:id>457</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Dimension reduction method of true proportional navigation guidance law]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201203001]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The dimension reduction method of the true proportional navigation (TPN) guidance law is proposed. Firstly, the rotation principle of the line of sight (LOS) was investigated, two kinds of angular velocities of LOS were presented, and so were their calculation methods. Then, the LOS kinematic equation was advanced, and the new relative dynamic equation between interceptor and target was proposed. It was found that there is an instantaneous rotation plane of LOS (IRPL) in the three dimensional (3D) space, in which two dimensional (2D) guidance laws can be constructed to serve for 3D interception guidance. The spatial 3D true proportional navigation (TPN) guidance law was directly introduced into IRPL without any approximation and linearization to transform into dimension reduced 2D TPN, and the characteristics were studied. Finally, an exoatmospheric interception was taken for simulation to demonstrate the effectiveness of the theory presented in this paper.]]></description>
<pubDate>2012/8/28 0:00:00</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LI Kebo,CHEN Lei and ZHANG Yi]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LI Kebo,CHEN Lei and ZHANG Yi</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201203001]]></guid><cfi:id>456</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[The enriched finite element method for 3-D fracture problems in viscoelastic materials]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201203002]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The enriched finite element method was developed for three dimensional fracture problems in a linear viscoelastic body. To manifest the singularity at the crack tip, the 8 node hexahedral enriched elements and corresponding transition elements were employed, combined with ordinary elements on the zone far away from the crack tip. Three types of elements were used together to form the whole mesh. Based on the boltzmann superposition principle, the incremental constitutive relation for viscoelastic materials was formulated. Furthermore, the incremental formulations of the enriched FEM were derived. The strain energy release rate in a cracked viscoelastic body was obtained through the enriched degree of freedoms. The numerical results show that the present method is accurate and efficient.]]></description>
<pubDate>2012/8/28 10:28:44</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[DUAN Jingbo and LEI Yongjun]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>DUAN Jingbo and LEI Yongjun</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201203002]]></guid><cfi:id>455</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[High-accuracy numerical method applied to calculate unsteady Euler equations]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201203003]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[By applying 5 order accuracy WCNS (Weighted Compact Nonlinear Schemes) to simulate forced oscillation of NACA0012 aerofoil, some techniques of high accuracy method in unsteady simulation were studied, such as inner iteration capability, inner iteration parameters of “dual time stepping” method, and discretization accuracy of time derivatives of Euler equations. The results show that, these coefficients have a remarkable effect on computation accuracy and CPU time when WCNS scheme is applied to unsteady flow simulation.]]></description>
<pubDate>2012/8/28 10:28:44</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[ZHAO Yunfei<sup>1</sup>,LIU Xu<sup>1</sup>,TU Guohua<sup>2</sup>,LIU Wei<sup>1</sup> and MAO Meiliang<sup>2</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>ZHAO Yunfei<sup>1</sup>,LIU Xu<sup>1</sup>,TU Guohua<sup>2</sup>,LIU Wei<sup>1</sup> and MAO Meiliang<sup>2</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201203003]]></guid><cfi:id>454</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Analysis and controller design of bank-to-turn system for hypersonic gliding vehicle]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201203004]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Bank-to-turn (BTT) technology is an important development direction of control technology for hypersonic gliding vehicles. This research focuses on the control system of bank-to-turn for the hypersonic gliding vehicle. By taking the equilibrium gliding trajectory as the reference trajectory, it analyzed the relationship between turn radius, falling height, and bank angle. The analysis shows that when designing the guiding and control command, the flight conditions and the limitation of the control ability need to be considered. Then the dynamics were separated into fast and slow variables in terms of singular perturbation theory. Furthermore, the trajectory linearization control (TLC) method was applied to design the control system. Simulation results show that the controller is robust and the command should be adjusted with the flight conditions to control the vehicle efficiently.]]></description>
<pubDate>2012/8/28 10:28:44</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[Chen Xiaoqing,Hou Zhongxi and Liu Jianxia]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>Chen Xiaoqing,Hou Zhongxi and Liu Jianxia</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201203004]]></guid><cfi:id>453</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Researches on teleoperation rendezvous and docking system]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201203005]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Teleoperation rendezvous and docking is referred to as the concept that the chase spacecraft is flown distantly through teleoperation approach. It can be used as a backup for autonomous rendezvous and docking for the unmanned chases during the finally approach stage. The concept of teleoperation rendezvous and docking (RVD) and the previous studies in this field were introduced firstly. Then, a design of the teleoperation RVD system was addressed, which is based on the primary assumed conditions of our future space station project. Finally, a simulation system was developed and corresponding experiments were carried out for verifying the design, especially the design with teleoperation time delay. The results show that the design is feasible, even though there are jobs to be done in the future.]]></description>
<pubDate>2012/8/28 10:28:44</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[ZHOU Jianyong,ZHANG Bo,JIANG Zicheng and LI Haiyang]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>ZHOU Jianyong,ZHANG Bo,JIANG Zicheng and LI Haiyang</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201203005]]></guid><cfi:id>452</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Longitudinal inversion control system designfor near-space vehicle]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201203006]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Near-space glide vehicle motion was modeled by nonlinear longitudinal dynamic equations. The Inverse system of this model was obtained by using dynamic inversion approach. The relative degree of dynamic model was equal to the rotational motion system order, so rotational motion dynamic model could be Input/Output linearization completely. The dynamic inversion method and optimal control were used in inner-loop and outer-loop for the longitudinal dynamic model. Simulation studies demonstrate that the proposed controller tracks the pitch angle or angle of attack command accurately, meets the performance requirements with acceptable control inputs and is robust with respect to the parametric uncertainties and external disturbance.]]></description>
<pubDate>2012/8/28 10:28:44</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[WANG Peng,LIU Luhua and WU Jie]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>WANG Peng,LIU Luhua and WU Jie</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201203006]]></guid><cfi:id>451</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Application of Radial Basis Function Network for Identification of Axial RLG Drifts in Single-axis Rotation Inertial Navigation System]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201203010]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In the single-axis rotation inertial navigation system with ring laser gyroscope (RLG), the single axis rotation can compensate the vertical errors of the inertial apparatus automatically, but cannot compensate the axial vertical errors, so the precision of the system is determined by the drift of the axial RLG. A novel identification method based on radial basis function network is proposed for the axial RLG drift. The inputs of the network are the latitude error and change of the temperature, and the network is trained for steady and non steady state, in which the identification capability is less than 0.0003°/h. The experiments show that this method can estimate the axial RLG drift efficaciously, and the result of the navigation is excellent and can meet the practical demand.]]></description>
<pubDate>2012/8/28 10:28:44</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[YU Xudong<sup>1</sup>,WEI Xuetong<sup>2</sup>,LI Ying<sup>2</sup> and LONG Xingwu<sup>1</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>YU Xudong<sup>1</sup>,WEI Xuetong<sup>2</sup>,LI Ying<sup>2</sup> and LONG Xingwu<sup>1</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201203010]]></guid><cfi:id>450</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Analysis of key technologies and development trend of near space vehicle]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201202023]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Integrative joint operation carries “land-sea-air-space-near space” five-in-one character. Near space has an important strategic status in the system combat based on information system, due to two advantages in information support and fast long distance delivery. Research progress of near space vehicle was summarized by considering technology factors. The key technologies and development trend of near space vehicle were analyzed. Several proposals about developing near space vehicle were provided. ]]></description>
<pubDate>2012/8/28 10:27:55</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[NIE Wansheng<sup>1</sup>,LUO Shibin<sup>2</sup>,FENG Songjiang<sup>1</sup> and ZHUANG Fengchen<sup>1,2</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>NIE Wansheng<sup>1</sup>,LUO Shibin<sup>2</sup>,FENG Songjiang<sup>1</sup> and ZHUANG Fengchen<sup>1,2</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201202023]]></guid><cfi:id>449</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Adaptive global integral sliding mode control for roll-channel of
 bank-to-turn hypersonic vehicle]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201202024]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Due to the large initial errors, uncertainties and disturbances in roll-channel of bank-to-turn hypersonic vehicle, an adaptive global integral sliding mode control approach is proposed. An adaptive parameter adjuster control rule was introduced into the sliding mode control, with the adaptive law adjusting parameter of the sliding mode controller to approximate the upper bound of parameter uncertainties and disturbances, which ensures the reachability of the sliding-mode during the whole control process. On the basis of this, an adaptive sliding mode control based on global integral sliding-mode is proposed. With this mode,  the steady-state tracking error was eliminated while the system lies on the sliding-mode from beginning of any initial state. It also can avoid large overshoots due to the large initial errors and can effectively weaken the dynamic influence of parameters uncertainties and disturbances. Theoretical analysis and simulation results show the effectiveness of the proposed global integral sliding mode control scheme.]]></description>
<pubDate>2012/8/28 10:27:55</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[XIONG Ke,XIA Zhixun and GUO Zhenyun]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>XIONG Ke,XIA Zhixun and GUO Zhenyun</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201202024]]></guid><cfi:id>448</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Lunar exact-landing trajectory optimization via the method
combining GPM with direct shooting method]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201202025]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Rapid lunar exact-landing trajectory optimization was studied by combining a new optimal control method-Gauss Pseudospectral Method (GPM) with the traditional direct shooting method. Landing dynamics equation in high precision model was educed. Aiming at the characters of optimization method and the difficulties in optimization of lunar soft landing trajectory with many constraints, a serial optimization strategy was proposed. Firstly, control variables and state variables were dispersed, and control variables and flying time were used as optimal variables. By giving fewer Gauss nodes, initial values were obtained using GPM, and a serial optimization framework was adopted to obtain the optimal solution from a feasible solution. Then the control variables were dispersed at Gauss nodes, the precise optimal solution was obtained by direct shooting method. Simulation results show that the methodology and strategy for the optimal trajectory design have good robustness and strong convergence.]]></description>
<pubDate>2012/8/28 10:27:55</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[PENG Qibo<sup>1,2</sup>,LI Haiyang<sup>1</sup>,SHEN Hongxin<sup>1,2</sup> and TANG Guojin<sup>1</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>PENG Qibo<sup>1,2</sup>,LI Haiyang<sup>1</sup>,SHEN Hongxin<sup>1,2</sup> and TANG Guojin<sup>1</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201202025]]></guid><cfi:id>447</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[The preliminary research of supersonic cruise missile master 
design based on penetration effectiveness]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201202026]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[New requirements for design of Supersonic Cruise Missile(SCM) have been brought forward with the technology development of defense systems. The technology of SCM general scheme design centering on a core of effectiveness was discussed preliminarily in this paper, considering the deficiency of traditional performance based design method for the new design requirements of SCM. Development of design technology for missile weapons abroad was firstly analyzed, and it is pointed out that the design technology is oriented toward a direction of effectiveness-centered design; the concept of effectiveness based design is brought forward, which is a certain kind of optimal design of pursuing a satisfying design; technology frame with penetration effectiveness based design was constructed under such new design concept. Main aspects were concentrated on the penetration effectiveness based SCM design frame, foundation of the penetration effectiveness, foundation of the technology, basic modes and several key technologies, etc.]]></description>
<pubDate>2012/8/28 10:27:55</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[FAN Yuzhu<sup>1,2</sup>,ZHANG Weihua<sup>1</sup>,WANG Zhongwei<sup>1</sup> and CHENG Jiantong<sup>1</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>FAN Yuzhu<sup>1,2</sup>,ZHANG Weihua<sup>1</sup>,WANG Zhongwei<sup>1</sup> and CHENG Jiantong<sup>1</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201202026]]></guid><cfi:id>446</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Study on coarse alignment method of airborne SINS]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201202027]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[An analytical method of coarse alignment in flight based on quaternion which can be used in landing system was presented without any restrictive condition of dynamic process and flight stability. The formula of the coarse alignment which can solve the attitude of the airplane with the velocity measured by GNSS and specific force measured by inertial measurement unit were derived. The factors affecting the alignment performance were analyzed. The simulation results show that the method can be carried out in wide dynamic range with high accuracy, high speed and low computer complexity and can satisfy the requirement of speed and .precision of flight coarse alignment.]]></description>
<pubDate>2012/8/28 10:27:55</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[CHEN Liang<sup>1</sup>,LI Hongtao<sup>2</sup> and WU Jie<sup>1</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>CHEN Liang<sup>1</sup>,LI Hongtao<sup>2</sup> and WU Jie<sup>1</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201202027]]></guid><cfi:id>445</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Research on equilibrium-glide state-feedback guidance 
method based on generalized reference-trajectory]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201202028]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[A new equilibrium-glide state-feedback guidance method based on generalized reference-trajectory was presented for the glide of long-range boost-glide vehicles, considering all path constraints. The 3DOF dynamic equations of boost-glide vehicles were established, and the path constraints were specified. Next, the principle of the guidance method was explained in detail. At the same time, the basis guidance law was designed, and its longitudinal parameter was set by LQR (linear quadratic reentry guidance methods), the new guidance method adjusted the trajectory by the change of angle of attract, and the bank angle profile was small through the glide phase. The simulations show that the new guidance method can satisfy the glide guidance problem of long-range boost-glide vehicles, and have the characteristics of being robust and adaptive. ]]></description>
<pubDate>2012/8/28 10:27:55</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LIU Jun,CHEN Kejun and Tang Guojian]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LIU Jun,CHEN Kejun and Tang Guojian</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201202028]]></guid><cfi:id>444</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Flutter analysis of hypersonic airfoil skin by differential quadrature method]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201202029]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Flutter analysis plays a vital role in the design of hypersonic airfoil skin. This research introduces the differential quadrature method into the aeroelastic problem of hypersonic skin. The aeroelastic model was presented based on the elasticity theory, and the hypersonic piston theory was used for the modeling of supersonic aerodynamic loads. The validity of the differential quadrature method was confirmed by comparing the FEM solutions for the natural frequencies and the flutter velocity of the airfoil skin, and the relative error is 0.58%. A detailed parametric study was carried out to study the influences of the thickness, area and aspect ratio on the hypersonic flutter behavior of airfoil skins. The result shows that, the flutter velocity increases with the aspect ratio and thickness increased, and decreases with the area increased. ]]></description>
<pubDate>2012/8/28 10:27:55</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[NIU Yaobin,WANG Zhongwei,MAO Jia and ZHANG Lixue]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>NIU Yaobin,WANG Zhongwei,MAO Jia and ZHANG Lixue</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201202029]]></guid><cfi:id>443</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Minimum mean square error bound for state estimation 
of maneuvering targets]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201306001]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The adaptive filtering algorithms based on the polynomial model are widely used in the field of maneuvering target tracking, but there is no uniform evaluation criterion to measure the quality of these tracking algorithms. Due to the existence of time-varying unknown inputs, the maneuvering target state estimation is actually biased. To solve this problem, the minimum mean square error bound calculation method for polynomial model Kalman filters was derived based on the minimum mean square error criterion, and the process noise variance law minimizing the state estimation mean square error was obtained. The proposed algorithm provides a unified evaluation standard for maneuvering target tracking algorithms based on the polynomial model, and also provides the basis for the setting of the actual process noise variance in maneuvering target tracking. The effectiveness of the proposed algorithm is demonstrated by the simulation results.]]></description>
<pubDate>2014/1/8 17:09:34</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[WU Nan<sup>1</sup>,CHEN Lei<sup>1</sup>,BO Tao<sup>2</sup> and LEI Yongjun<sup>1</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>WU Nan<sup>1</sup>,CHEN Lei<sup>1</sup>,BO Tao<sup>2</sup> and LEI Yongjun<sup>1</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201306001]]></guid><cfi:id>442</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[High order upwind compact schemes based on TVD algorithm]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201306002]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Using the same stencils, the compact schemes can get higher accuracy and resolution compared with the traditional ones. But it will bring about spurious oscillations if the compact schemes are used directly. There are several methods to settle this problem. The TVD algorithm was selected in our study. Firstly, two five-order upwind compact schemes were introduced and Fourier analysis was used to compare their dissipation and dispersion characteristics. Secondly, two different TVD methods were applied to Euler equations. The performance of the numerical algorithm was assessed by performing preliminary simulations on some problems, such as the oblique shock reflection problem. The algorithm applied here is proven to have good resolution properties and robust of capturing shock waves and contacts, but it still has the problems of accuracy degree and lack of dissipation.]]></description>
<pubDate>2014/1/8 17:09:34</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[WANG Wenlong,LI Hua,LIU Feng and TIAN Zhengyu]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>WANG Wenlong,LI Hua,LIU Feng and TIAN Zhengyu</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201306002]]></guid><cfi:id>441</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Fault diagnosis method for liquid-propellant rocket 
engines based on the cloud sorter]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201306003]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Through transforming the fault diagnosis into the pattern classification of fault characteristics, a fault diagnosis method was developed, based on the cloud sorter for liquid-propellant rocket engines. The method synthesized the study on cloud model and the cloud transform, which can deal with the uncertainty and the hard partition of domain boundary for the quantitative attributes which exist in the traditional classification methods. Caculation results with test data show that the method can recognize the fault modes in the startup process of the engine timely and precisely.]]></description>
<pubDate>2014/1/8 17:09:34</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[PENG Xiaohui,LIU Yinjie,CHENG Yuqiang and WU Jianjun]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>PENG Xiaohui,LIU Yinjie,CHENG Yuqiang and WU Jianjun</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201306003]]></guid><cfi:id>440</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Fast unstructured mesh generation based on arbitrary polyhedron]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201306004]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Mesh generation is the key to the numerical simulation in CFD with complex aerodynamic shapes. The algorithm of mesh generation is required to be fast and robust. First, this framework established efficient initial tetrahedron arithmetic based on viewed-able face which is fit to the arbitrary polyhedron. Then, Delaunay generation method was improved to refine meshes and the effect of different mesh quality criterion was discussed and the divergence with Delaunay face swapping was developed to optimize the mesh generation process, Finally, a vertex spring model for mesh optimization was established. The results indicate that the method established in the research is efficient and stable.]]></description>
<pubDate>2014/1/8 17:09:34</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LIU Feng,LI Hua,TIAN Zhengyu and PAN Sha]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LIU Feng,LI Hua,TIAN Zhengyu and PAN Sha</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201306004]]></guid><cfi:id>439</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Optimal guidance with maneuver for hypersonic 
vehicle in dive phase]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201306005]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[To solve precise guidance and maneuver penetration problems for hypersonic vehicle in dive phase, the optimal guidance method with maneuver was proposed. Considering that the traditional guidance law based on zero-LOS angle rate can debase penetrative ability, it designed reference motion for the rate in diving-plane and turning-plane. Besides, in order to enhance penetrative ability farther and realize precise guidance, it took advantage of optimal control with the optimal index of maximum terminal velocity to track the LOS angle rate, and pseudo control variable was introduced to simplify the resolution of optimal control problem. Finally, it analyzed the guidance capability and stability of this method. The results of CAV-H vehicle test show that the algorithm can realize maneuvering flight, and can satisfy terminal impact point and falling angle constraints. Therefore, the method can offer reference for high precision guidance and maneuver penetration for hypersonic vehicle in dive phase.]]></description>
<pubDate>2014/1/8 17:09:34</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[ZHU Jianwen<sup>1</sup>,LIU Luhua<sup>1</sup>,TANG Guojian<sup>1</sup> and BAO weimin<sup>2</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>ZHU Jianwen<sup>1</sup>,LIU Luhua<sup>1</sup>,TANG Guojian<sup>1</sup> and BAO weimin<sup>2</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201306005]]></guid><cfi:id>438</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Thermal analysis of refractive secondary concentrator of 
solar thermal thruster based on regenerative cooling]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201306006]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Solar thermal propulsion is a high efficiency propulsion system, utilizing concentrated sunlight radiation to heat low molecular weight working fluid and providing high specific impulse. With regenerative cooling, an integration of the second concentrator and thruster can cool down the former to 1600K and preheat the propellant to 600K, thus improving the energy conversion efficiency of the propulsion system. The thermal radiation simulation shows that the flowing propellant is of little influence on the cavity temperature and the cavity can maintain high temperature between 2400K and 2600K.]]></description>
<pubDate>2014/1/8 17:09:35</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[XING Baoyu,LIU Kun,HUANG Minchao and CHENG Mousen]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>XING Baoyu,LIU Kun,HUANG Minchao and CHENG Mousen</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201306006]]></guid><cfi:id>437</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[A method about backstepping control for waverider slide 
hypersonic vehicle with large envelope]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201306007]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Waverider slide hypersonic vehicle will be very useful for transport and even a powerful weapon in the future. The flight environment is very complex as the hypersonic vehicle flies at high speed and covers wide range, thus the control system of the hypersonic vehicle must have good adaptability. As decoupling pseudolinear system does not have fine dynamic performance, this research established the attitude model of the hypersonic vehicle, using the discoupling method and Block Backstepping theory to design the control system. The stability of close-loop system was proved and the simulation with large flight envelope and large-scale parameters perturbation was accomplished. The results showed that the method can ensure the stability of close-loop system's Lyapunov functions. With functional agility and rapid response, the control system can solve the problem brought about by large flight envelope and large-scale parameters perturbation, and can enhance the system's robustness.]]></description>
<pubDate>2014/1/8 17:09:35</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LI Jian,ZHANG Weihua and ZHENG Wei]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LI Jian,ZHANG Weihua and ZHENG Wei</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201306007]]></guid><cfi:id>436</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Adaptive fuzzy sliding mode stabilization control for 
floated inertial platform]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201306008]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[A control algorithm of adaptive sliding mode control based on fuzzy logic is proposed for the inertial stabilization problem of the floated inertial platform (FLIP). The sliding mode control was used to solve the parameters uncertainness and unmodeled dynamics of the FLIP, which guarantees the stability and rapidity of the system. Then, by focusing on the design problem of the sliding mode control, the gain of a sliding mode control was adjusted by using the fuzzy logic with an adaptive tuning algorithm，which enhanced the adaptability for random uncertainty and improved the robust performance and the stabilization accuracy of the controller. Finally, the stability and convergence of the control system were proven by using the Lyapunov method．The simulation results demonstrate that the proposed method can eliminate the input chattering of the sliding mode control efficiently, and the inertial stabilization of the FLIP is realized with the accuracy higher than 0.1 ″.]]></description>
<pubDate>2014/1/8 17:09:35</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LI Anliang,CAI Hong and BAI Xibin]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LI Anliang,CAI Hong and BAI Xibin</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201306008]]></guid><cfi:id>435</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Multiplicative filtering for spacecraft attitude determination]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201306009]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Multiplicative extended Kalman filter (MEKF) has been widely applied in the vast majority of spacecraft attitude determination missions. For the arbitrary reference frame, the linear quaternion kinematics equation and the dynamical model of three-component attitude errors were formulated, and gyro-aided and gyro-free attitude determination schemes were designed. The typical basic equation of the MEKF was developed, including the detailed models for vector measurements, quaternion measurements and Euler angle measurements. The research can provide theory reference and technique support for spacecraft missions.]]></description>
<pubDate>2014/1/8 17:09:35</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[ZHANG Lijun<sup>1</sup>,ZHANG Shifeng<sup>1</sup>,YANG Huabo<sup>1</sup> and QIAN Shan<sup>2</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>ZHANG Lijun<sup>1</sup>,ZHANG Shifeng<sup>1</sup>,YANG Huabo<sup>1</sup> and QIAN Shan<sup>2</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201306009]]></guid><cfi:id>434</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Study on the flow fields of supersonic mixing layer with 
splitters of different geometric configurations]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201305001]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Through combining an experiment and a numerical simulation, a study was carried out on supersonic mixing layer with splitters of different geometric configurations, which is under the condition of  Ma<sub>1</sub>=1.5，Ma<sub>2</sub>=2.5，T<sub>0,1</sub>=300K，T<sub>0,2</sub>=1200K，and matched pressure p<sub>1</sub>=p<sub>2</sub>=86kPa.In the experiment, it was discovered that the thickness of mixing layer in the flow field with splitters in which a cavity is mounted grows as the ratio of the length to the depth of the cavity becomes larger; Splitters with sawtooth trail show great effect of mixing enhancement and making the flow field highly unsteady. In the numerical study, it was demonstrated that the mixing-enhancement effect of splitters with cavity is due to the cavity shear layer’s reattachment to the trail of the splitter, and splitters with sawtooth trail due to induced large-scale streamwise vortexes. ]]></description>
<pubDate>2013/11/6 15:57:50</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LIU Yu,ZHOU Jin and YAN Zhihui]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LIU Yu,ZHOU Jin and YAN Zhihui</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201305001]]></guid><cfi:id>433</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Optimizing design of clamp band joint based on 
parameter modeling method]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201305002]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[A new application based on the parameter modeling method of MSC.Patran and generation algorithm was proposed to design the clamp band joint. First, finite element techniques for 2-dimension axisymmetric analysis of clamp band joints were developed, including the modeling of V-clamp, strap pre-tension and loads, and the optimizing constrains and objectives were also introduced. Then a clamp band joint with the diameter being 3m was designed via the presented method. Finally, a 3-dimension finite element model of the designed clamp band joint was established and analyzed. It indicates that the method is applicable to the design of clamp band joints, that the connective stiffness is strengthened by increasing the length and height of the inner ring of the interface rings, and that the modeling method is proved to be valid by the agreements of the finite element analysis results of 2-D model and 3-D model.]]></description>
<pubDate>2013/11/6 15:57:50</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[WU Xinfeng<sup>1</sup>,LIU Guanri<sup>1,2</sup>,LEI Yongjun<sup>1</sup> and LI Jin<sup>1</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>WU Xinfeng<sup>1</sup>,LIU Guanri<sup>1,2</sup>,LEI Yongjun<sup>1</sup> and LI Jin<sup>1</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201305002]]></guid><cfi:id>432</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Laminar combustion model of pulverized magnesium particle cloud in powdered fuel ramjet
]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201305003]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The combustion process of pulverized magnesium particle cloud in powdered fuel ramjet preburner was studied and a one-dimension premixed laminar combustion model of pulverized magnesium particle cloud was established. The study shows that the laminar flame propagation of pulverized magnesium particle cloud is very stable, and the flame structure is almost invariable in the combustion process; the combustion zone thickness is very thin and the preheat zone thickness is about 2-3 times as much as the former. The magnesium particles vaporization and the homogeneous reaction of magnesium vapor and oxygen in particle cloud is the direct cause of flame and the key of flame propagation that; the preheat zone gas temperature rising depends mainly on the thermal conductivity of the combustion zone and the reaction heat of magnesium vapor which diffuses from combustion zone and oxygen while the preheat zone particle temperature rise depends on the convective heat transfer from gas phase to particle phase mostly. The effects of the interior parameters on the combustion of the magnesium particle cloud were analyzed. The effect of particle relative concentration on combustion of particle cloud is complex. When the particle relative concentration is low, increasing particle relative concentration is helpful for speeding up the particle cloud combustion process; when the particle relative concentration is high, increasing particle relative concentration is adverse to speeding up the particle cloud combustion process. With the increase of the particle size, the flame propagation speed is reduced, the flame temperature increases, and the thickness of preheat zone increases as well. With the increase of the initial temperature of particle cloud, flame propagation speed and flame temperature display linear growth, and the preheat zone thickness shows parabolic growth. The tendencies obtained by numerical simulation coincide well with those of the experimental results from the previous literature.]]></description>
<pubDate>2013/11/6 15:57:50</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[YANG Jinzhao,XIA Zhixun and HU Jianxin]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>YANG Jinzhao,XIA Zhixun and HU Jianxin</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201305003]]></guid><cfi:id>431</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[A fault diagnosis approach research based on LPS model 
for flight control system]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201305004]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The traditional fault diagnosis method is generally based on the measuring signal, without considering the actual physical connection characteristics, but these characteristics affect the diagnosis results. With the wide application of professional electric system design software, system designers can easily obtain the physical connection characteristics and logical connection characteristics. By analyzing the signals of product layer or system layer, physical connection and its interconnected relationship, a set of logical physical synthetically (LPS) model, which unifies the abstract signal and the physical connection, was presented to study the LPS model instantiation method based on wire table and net table, and a set of intelligent fault detection software was developed. An example for validation was demonstrated: the fault diagnosis method based on LPS model can isolate the fault to the specified product level, with great value of engineering application.]]></description>
<pubDate>2013/11/6 15:57:50</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[ZENG Qinghua,HUANG Zhezhi,JIA Tao and CHEN Longzhi]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>ZENG Qinghua,HUANG Zhezhi,JIA Tao and CHEN Longzhi</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201305004]]></guid><cfi:id>430</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Research on mission assignment of on-orbit servicing spacecraft]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201305005]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[One mission of on-orbit servicing can be fulfilled in many ways, and proper mission assignment must be guaranteed. In light of this, first, the reachable domain of service spacecraft was resolved and the target spacecraft which satisfies the reachable domain was filtered. Then the assignment of servicing based on the optimization of multi-objective, including time, fuel consumption and priority, was studied. The best plan was achieved by building the model of 0-1 integer programming and taking the NSGA-Ⅱ algorithm with the constraint of time and fuel consumption. Finally two examples of simulation were given, one demonstrating the general results of the above method, either compared with another algorithm. The simulation results indicate that the above method is effective in solving the problem of mission assignment for on-orbit servicing.]]></description>
<pubDate>2013/11/6 15:57:50</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LIANG Yangang and WANG Weilin]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LIANG Yangang and WANG Weilin</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201305005]]></guid><cfi:id>429</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[The method for orbit determination of single 
satellite observation based on constringent estimation]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201305006]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Feasibility of Space-based Tracking Telemetry and Command System (TT&C) based on single satellite was analyzed. A new orbit determination method based on constringent estimation was proposed according to the mode of single satellite observation. In the process of the orbit determination, the law matrix was availably transformed by the constringent estimation to restrain error of singularity cased by law matrix. It was proved that the precision of constringent estimation is higher than the traditional method under the given conditions. Then the error transmitting coefficient (ETC) of observation was proposed, on the basis of the special characteristics of the single satellite observation, and the algorithm of orbit determination was designed. Finally the new method of constringent estimation was proved to be able to improve the precision of orbit determination in the mode of single satellite observation.]]></description>
<pubDate>2013/11/6 15:57:50</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[PAN Xiaogang<sup>1，2</sup>,LIU Jing<sup>3</sup>,WANG Jiongqi<sup>1</sup> and ZHOU Haiyin<sup>1</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>PAN Xiaogang<sup>1，2</sup>,LIU Jing<sup>3</sup>,WANG Jiongqi<sup>1</sup> and ZHOU Haiyin<sup>1</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201305006]]></guid><cfi:id>428</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[The weekly task scheduling model and solving algorithm 
of imagining satellites]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201305008]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Satellite weekly task scheduling is an important procedure for the Satellite Run and Management System, and it exerts influence on the effectiveness of satellite system. Different from the function and the characteristics of daily task scheduling, weekly task scheduling includes not only the technology problem but also the management problem. This study mainly expounds three aspects of work: firstly, analyzing the demand and the characteristic of weekly task scheduling, explaining four main functions of weekly scheduling, and constructing a hierarchical scheduling framework; secondly, summarizing optimization objects and constraint conditions, and building the weekly task scheduling model with considering the task overloading factor; thirdly, combing the Gene Algorithm and the Simulated Annealing Search to solve the model, while instigating the heuristic rules and introducing distributed parallel computing strategy.]]></description>
<pubDate>2013/11/6 15:57:50</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[PANG Xiuli<sup>1，2</sup>,YU Bo<sup>1</sup> and JIANG Wei<sup>1</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>PANG Xiuli<sup>1，2</sup>,YU Bo<sup>1</sup> and JIANG Wei<sup>1</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201305008]]></guid><cfi:id>427</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Numerical analysis of plume field of a pulsed plasma thruster]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201305011]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Considering the effect of magnetic field on the plasma plume, a hybrid particle-fluid model combining DSMC and PIC methods was developed to study the plume characteristics of a pulsed plasma thruster. By incorporating a magnetohydrodynamic code to provide inlet conditions, this model was applied to simulate the three-dimensional plume field. The calculation results were validated by an experiment based on triple Langmuir probes. Investigations show that there are substantial differences between the expansion dynamics of various species. It is indicated that the oscillation of discharge current will lead to the generation of a population of low-velocity ions, together with the aggravation of backflow of ions. Electromagnetic acceleration is demonstrated to be the primary mechanism of plasma acceleration, and the magnetic field plays an important role in the diffusion of the thruster plume.]]></description>
<pubDate>2013/11/6 15:57:51</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[XIE Zehua,ZHOU Jin,ZHANG Rui and LI Ziran]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>XIE Zehua,ZHOU Jin,ZHANG Rui and LI Ziran</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201305011]]></guid><cfi:id>426</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Feedback control method for attitude maneuver of 
agile satellite based on trajectory optimization]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201304001]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Rapid actuation is needed to avoid singularity state in the single-gimbal control moment gyros (SGCMG) steering logic. It consumes significant energy and produces danger for system. A novel control method for attitude maneuver combined trajectory and feedback control is proposed. Firstly, to avoid the singularity state, the pseudospectral method was used to solve the energy optimization issue. Then optimal solution of control acted as reference input, and feedback control method based on the system's limit state was used to consider the effect of uncertainty and disturbances. Feedback control predicted the state based on the numerical integration of reference input, and the error was based on the comparison of the designed state and the predicted state. Numerical simulation was carried out to verify the feasibility of the proposed method, which shows that it can avoid the singularity state, and is valid to overcome the error of the initial velocity of satellite and gimbal angular of SGCMGs. ]]></description>
<pubDate>2013/8/22 16:54:27</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[FENG Zhiwei<sup>1</sup>,ZHANG Yonghe<sup>2</sup>,LIU Zhichao<sup>1</sup>,ZHANG Qingbin<sup>1</sup> and TANG Qiangang<sup>1</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>FENG Zhiwei<sup>1</sup>,ZHANG Yonghe<sup>2</sup>,LIU Zhichao<sup>1</sup>,ZHANG Qingbin<sup>1</sup> and TANG Qiangang<sup>1</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201304001]]></guid><cfi:id>425</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Study of control momentum gyroscopes assisting maneuver]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201304002]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Control Momentum Gyroscopes Assisting Maneuver (CMGs AM) technique, a new large-angle space station attitude maneuver technique concept, is proposed, which employs both the Control Moment Gyroscopes (CMGs) and the thruster Reaction Control System (RCS) as the actuator. The fuel- optimal control problem of CMGs AM is formulated. With a two-step solving strategy, which utilizes an improved pseudo spectral knotting method, the fuel-optimal solution was obtained, and the results were compared with the fuel-optimal solution and constant-rate eigenaxis maneuver of thrust maneuver technique. It is shown that the CMGs AM technique inherits and further enhances the advantages of thruster maneuver and Zero Propellant Maneuver (ZPM) techniques. It significantly saves more fuel than the thrust maneuver and shortens the maneuver time greatly with greater robustness in comparison with ZPM.]]></description>
<pubDate>2013/8/22 16:54:27</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[ZHANG Sheng,HUANG Haibing,ZHAO Qian and TANG Guojin]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>ZHANG Sheng,HUANG Haibing,ZHAO Qian and TANG Guojin</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201304002]]></guid><cfi:id>424</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Fluid-solid coupled heat transfer and flow simulation of 
platelet heat exchanger in thermal thruster]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201304004]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Thermal propulsion system includes solar thermal propulsion and nuclear thermal propulsion, and it is a significant issue to improve the heat transfer efficiency of the thermal thruster. Based on the fluid-solid coupled heat transfer, this study utilized the platelet heat transfer characteristics to simulate the heat transfer and flow field of the platelet passage. A coupled system included both the coupled flow and the heat transfer between fluid and solid parts, in addition to the coupled heat transfer among solid parts. Simulation result shows that the fluid-solid coupled method can solve the steady heat transfer in the platelet structure, and the propellant can be heated to the design temperature of 2300K for the thermal propulsion system. ]]></description>
<pubDate>2013/8/22 16:54:27</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[XING Baoyu,CHENG Mousen,HUANG Minchao and LIU Kun]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>XING Baoyu,CHENG Mousen,HUANG Minchao and LIU Kun</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201304004]]></guid><cfi:id>423</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[On modeling and denoising of X-ray pulsars profile]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201304005]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The pulsar profile, which is the key measurements of the pulsar navigation, is an important physical property of the pulsar. For in-depth study of the theoretical properties of the pulsar profile, the mathematical models of the standard pulsar profile and of the observed pulsar profile were established. The Crab Nebula profile function was fitted using the exponential function and the crab nebula standard pulsar profile was simulated using the profile function. Through the simulation of non-homogeneous Poisson random shooting experiment, the value of the photons TOA (time of arrival) was obtained, and the observed pulsar profile of the Crab Nebula was simulated. The simulation results show that the model can well describe the pulsar profile of the sky survey. The observed pulsar profile which was comprised of the profile and the noise was denoised based on wavelet threshold denoising method. Compared with the wavelet thresholding denoising method, through the numerical analysis, the GCV has a better denoising effect for the observed pulsar profiles.]]></description>
<pubDate>2013/8/22 16:54:28</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LI Shengliang,LIU Kun and WU Jinjie]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LI Shengliang,LIU Kun and WU Jinjie</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201304005]]></guid><cfi:id>422</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Experimental research on operation performance of 
kerosene heater based on combustion heating]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201304006]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In order to satisfy the demand of ground tests of ramjet, a kerosene heater based on gas heating was designed, and tests were taken to do research on the influence of several factors on the operation performance. The results indicate that the kerosene heater has a strong ability of heating, less responding time, and it can produce supercritical/cracked kerosene online; the main factors that influence operation performance of kerosene heater are temperature, mass flow rate of gas, and mass flow rate of kerosene. The kerosene heater can accommodate temperature of kerosene in a large range through control of temperature and mass flow rate of gas. Then it can satisfy demand of different status of ramjet ground tests.]]></description>
<pubDate>2013/8/22 16:54:28</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[ZHANG Jianqiang,ZHONG Zhan,DING Meng and LI Qinglian]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>ZHANG Jianqiang,ZHONG Zhan,DING Meng and LI Qinglian</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201304006]]></guid><cfi:id>421</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Experimental researches on ignition characteristic of 
air/kerosene/water gas generator]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201304007]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The gas generator is the key equipment of scramjet ground test system. A kind of air/kerosene/water gas generator was designed in order to improve the system security and economy. A series of ignition performances experiments were conducted in the fuel-rich condition with the gas generator. The experimental results indicate that: the lower limit of excess oxidizer coefficient for reliable ignition was 0.51 with the gas generator. The injection of water, which lowered the flame propagation speed and reduced the chemical reaction rate, would make it difficult to ignite and stabilize the flame. The ignition reliability could be improved by increasing excess oxidizer coefficient. Simultaneously, the injection of water would easily cause combustion instability. Low frequency combustion instability can be damped by increasing excess oxidizer coefficient.]]></description>
<pubDate>2013/8/22 16:54:28</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[ZHANG Xinqiao,LI Qinglian and Kang Zhongtao]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>ZHANG Xinqiao,LI Qinglian and Kang Zhongtao</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201304007]]></guid><cfi:id>420</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Attitude control using thrusters based on slantwise 
on-off switching line and modified limit circle control]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201304008]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The attitude control problem of a satellite using small thrusters was investigated. With a simulation example, the drawbacks of control method using slantwise on-off switching line proposed in the relevant reference were discussed. A necessary and sufficient condition for an ideal limit circle was deduced theoretically in the case that the desired attitude precision and the parameters of thrusters and slantwise on-off switching line were known previously. Analysis on the case that the ideal limit circle cannot be formed was also conducted. Based on these analyses, a new control method called "Modified Limit Circle Control" was proposed as well as its design procedure. This study can provide meaningful reference for some relevant engineering applications.]]></description>
<pubDate>2013/8/22 16:54:28</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[WEI Jingbo,LIU Kun and WU Jinjie]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>WEI Jingbo,LIU Kun and WU Jinjie</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201304008]]></guid><cfi:id>419</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Dynamic mesh based airfoil design optimization]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201302001]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[According to the drawbacks of traditional surrogate model based airfoil optimization, dynamic mesh based airfoil design optimization was studied. Hicks-Henne parameterization method was improved against the drawbacks of unsmooth tailing edge, which was subsequently utilized for the construction of airfoil dynamic mesh. Commercial software Pointwise and Fluent were integrated by secondary development, which automates the adding boundary condition and CFD calculation. The data flows and work flows between commercial software and programs were realized under iSIGHT platform. An airfoil optimization case study shows that the method can significantly improve aerodynamic performance of airfoils, and save massive repeat operations, which is verified an effective and high efficient method of airfoil design optimization. ]]></description>
<pubDate>2013/5/21 9:27:54</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[ZHU Xiongfeng,GUO Zheng,HOU Zhongxi and CHEN Xuekong]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>ZHU Xiongfeng,GUO Zheng,HOU Zhongxi and CHEN Xuekong</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201302001]]></guid><cfi:id>418</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Theoretic analysis and numerical simulation of coefficient of pressure center of body of slender revolution at high-angle-of-attack]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201302002]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The relationship of coefficient of pressure center of body of revolution and angle-of-attack and Mach number was educed, based on the aerodynamic formulas of high-angle-of-attack flow. Adopting a k-ε two-equation turbulence model following the realizable rules, seven kinds of body of revolution with different shapes in high-angle-of-attack flow fields were researched by means of CFD, and the numerical results were derived. The numerical simulation results were consistent with the ones in theoretic analysis. Research results indicate that there is a geometric discriminant, which is correlated with the geometric configuration that has strong influence on the law of variation of the coefficient of pressure center. ]]></description>
<pubDate>2013/5/21 9:27:54</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[MA Yang<sup>1</sup>,WANG Lei<sup>1</sup>,WANG Dandan<sup>2</sup>,YANG Tao<sup>1</sup> and ZHANG Qingbin<sup>1</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>MA Yang<sup>1</sup>,WANG Lei<sup>1</sup>,WANG Dandan<sup>2</sup>,YANG Tao<sup>1</sup> and ZHANG Qingbin<sup>1</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201302002]]></guid><cfi:id>417</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Algorithm for the pulsar timing system with the system bias]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201302003]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The rotating period of the pulsars are highly stable, and the measurement of the pulsars can be adopted to correct the clock error of the satellite-borne atomic clock. In order to solve the problem that the minor system bias can largely worsen the performance of the pulsar timing system, an algorithm for the pulsar timing system with the system bias is proposed. Based on the principle of the pulsar timing system, the system bias was modeled. By using the two-stage Kalman filter, the system state and the system bias were decoupled and estimated. The results of the simulations show that the proposed algorithm can effectively reduce the impact of the system bias and can improve the performance of the pulsar timing system. ]]></description>
<pubDate>2013/5/21 9:27:54</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[WANG Yidi<sup>1</sup>,ZHENG Wei<sup>1,2</sup>,SUN Shouming<sup>3</sup> and AN Xueying<sup>1</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>WANG Yidi<sup>1</sup>,ZHENG Wei<sup>1,2</sup>,SUN Shouming<sup>3</sup> and AN Xueying<sup>1</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201302003]]></guid><cfi:id>416</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Effect of impingement angle and wall curvature on liquid film]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201302004]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Impingement angle and wall curvature are important for liquid film cooling design of liquid rocket engine. The effect of impingement angle and wall curvature on film form and thickness was studied experimentally. The film thickness was calculated by contact needle method. Splash occurred with high Webber number during impingement. The critical Webber number for transformation from adherent to splash is 
214.1, and the critical impingement angle is 23.1°, which means the impingement angle can be optimized for different liquid rocket engines.]]></description>
<pubDate>2013/5/21 9:27:54</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LIN Qingguo<sup>1,2</sup>,YANG Chenghu<sup>2</sup> and LIU Ben<sup>2</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LIN Qingguo<sup>1,2</sup>,YANG Chenghu<sup>2</sup> and LIU Ben<sup>2</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201302004]]></guid><cfi:id>415</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Research of fault component isolation algorithms for LRE base on fuzzy model]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201302005]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Fault detection and diagnosis is a difficult problem in liquid-propellant rocket engines (LRE) healthy monitoring, but it has important significance for locating an engine fault, preventing tragedy accident from occurring, and maintaining engines. So a fault isolation method in components level based on fuzzy model was proposed to confirm the position of the fault for certain Liquid-propellant rocket engines. Firstly, it divided the engine into several components; secondly the fuzzy model for each component was established and trained; finally the method performed fault diagnosis according to established strategy. The fault isolation algorithm based on fuzzy model was validated by two sets of simulation data. The results indicate that fault isolation algorithm can isolate single fault or multi fault components effectively. ]]></description>
<pubDate>2013/5/21 9:27:54</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LI Yanjun,PENG Xiaohui,CHENG Yuqiang and WU Jianjun]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LI Yanjun,PENG Xiaohui,CHENG Yuqiang and WU Jianjun</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201302005]]></guid><cfi:id>414</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Nonlinear filter algorithm for micro satellite attitude determination 
via magnetometer and fiber optic gyroscope]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201301001]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[A new nonlinear filter algorithm for micro satellite attitude determination was proposed, which adopted three-axis magnetometer(TAM) and fiber optic gyroscope(FOG) as attitude sensors. In the design of the nonlinear filter, square-root sigma point Kalman filter was modified. Firstly, an augmented state vector was derived by combining the vector part of attitude quaternion, the bias and noises of FOG. Secondly, vector rotational model, optimization model and error quaternion multiplication model were established to guarantee the quaternion normalization constraint in the process of nonlinear filter. The simulation results indicate that attitude determination performance is improved effectively by the presented algorithm. In comparison with EKF, the accuracy and stability of the proposed algorithm is much better, and the convergent speed is faster. In comparison with UKF, the convergence is equivalent, the accuracy is slight better, while the stability and computing efficiency are both higher.]]></description>
<pubDate>2013/3/13 9:54:33</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[WU Jinjie<sup>1</sup>,LIU Kun<sup>1</sup>,SHI Shi<sup>2</sup> and ZHANG Binbin<sup>1</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>WU Jinjie<sup>1</sup>,LIU Kun<sup>1</sup>,SHI Shi<sup>2</sup> and ZHANG Binbin<sup>1</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201301001]]></guid><cfi:id>413</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Modelling and analysis of a hypersonic vehicle with aeroelastic effect]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201301002]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Hypersonic vehicle can be designed into blended lift body by using light-weighted materials, which leads to close frequencies between controlled rigid-body motion and the oscillation of the structure. It brings about a huge challenge in the design of guidance and control system. Based on the assumed mode method, the free-free beam structural dynamics model considering variable cross-section effect was built. After comparing the mode shape and frequencies between cross-section and variable cross-section beam, it is found that the later one had a bigger mode shape change, and the frequency of second and three order both decreased. Given the hypersonic vehicle equations, the static and dynamic characteristics of constant cross-section and variable cross-section beam were analyzed in a typical condition. The results indicate that the variable cross-section beam has a larger appended angle of attack, the system is open-loop unstable, and exhibits non-minimum phase behavior in the trim condition.]]></description>
<pubDate>2013/3/13 9:54:33</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LI Jianlin,TANG Qiangang,FENG Zhiwei,YANG Tao and LIU Zhichao]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LI Jianlin,TANG Qiangang,FENG Zhiwei,YANG Tao and LIU Zhichao</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201301002]]></guid><cfi:id>412</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Convergence analysis and application of the slip boundary conditions]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201301003]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[By replacing the typical no-slip boundary conditions with velocity slip and temperature jump boundary conditions, the predicting accuracy of the CFD modeling is improved effectively for high altitudes flow in the slip regime. The numerical iterations usually suffer form divergence when the Maxwell slip boundary conditions are implemented with very great number of grid points by the numerical method, which the velocity slip and temperature jump are evaluated through explicit calculation of the velocity and temperature gradient terms. In the theoretical analysis, it is shown that the explicit calculation of gradient terms displays the time advancement process of the Maxwell slip boundary conditions similar to a Jacobian iteration scheme, hence it must satisfy the condition of convergence. In order to remove the limitation from the condition of convergence, a numerical treatment which is convergent for arbitrary grid density was derived for the slip boundary conditions. Numerical tests were calculated to demonstrate the validity of the derived method. A space shuttle model was studied numerically for hypersonic flow at high altitudes. The results disagreement between the slip and no-slip conditions was compared and the influence of slip effects on vehicle aerodynamic characteristics and aerothermodynamic properties was analyzed.  ]]></description>
<pubDate>2013/3/13 9:54:33</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[CAO Wenbin,LI Hua and GAO Honghe]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>CAO Wenbin,LI Hua and GAO Honghe</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201301003]]></guid><cfi:id>411</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Research on the real-time calculation of  perturbation guidance coefficients for the launch vehicle]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201301004]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The guidance precision of the launch vehicle during the flight stage within the atmosphere is greatly affected by the guidance coefficients of perturbation guidance. However, there is no comparable database for the guidance coefficients selection in the argumentation of a new launch vehicle, which cannot meet the demand for rapid calculation using the traditional test method. A real-time calculation method for the guidance coefficient which considers both the real-time status and the follow-up flight trajectory is proposed, based on introducing the concept of remaining flight speed in the standard trajectory. Through the numerical simulation, it is proved that higher guidance precision is achieved by the proposed method in comparison with the traditional method with constant coefficients. Since the guide capacity was predicted by this method, the guidance instruction do not change dramatically, which contributes to easy design for the attitude control system. Meanwhile, a fully analytical method was developed, so there is no additional calculation requirement for the rocket-born computer, giving rise to convenient engineering realization.]]></description>
<pubDate>2013/3/13 9:54:33</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[HUANG Wenbo<sup>1,2</sup>,ZHANG Yinhui<sup>1</sup>,SHI Shuai<sup>2</sup> and ZHANG Weihua<sup>1</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>HUANG Wenbo<sup>1,2</sup>,ZHANG Yinhui<sup>1</sup>,SHI Shuai<sup>2</sup> and ZHANG Weihua<sup>1</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201301004]]></guid><cfi:id>410</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Viscoelastic cumulative damage of dolid propellant grain based on energy dissipation]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201301005]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[A cumulative damage model of solid propellant was established based on energy dissipation damage variable defining method and dynamic linear viscoelastic theory. The expression of dissipated energy when destroyed was obtained according to the experimental data of different stretch rates, and the formula of cumulative damage for grain was presented as well. Considering influence of circular stress magnitude and frequency, the rule of cumulative damage varying was researched respectively, and a case of cumulative damage and life prediction for solid rocket motor grain was analyzed finally. The method is beneficial for the storage life prediction of solid rocket motor.]]></description>
<pubDate>2013/3/13 9:54:33</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[DENG Bin<sup>1</sup>,DONG Kehai<sup>2</sup> and XIE Yan<sup>1</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>DENG Bin<sup>1</sup>,DONG Kehai<sup>2</sup> and XIE Yan<sup>1</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201301005]]></guid><cfi:id>409</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Midcourse guidance law optimal design for air-to-air missiles based on gauss pseudospectral method]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201301006]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The optimum design of midcourse guidance law for air-to-air missiles was researched based on Gauss Pseudospectral Method (GPM). The optimal control model for midcourse guidance law of air-to-air missiles was established, the idea to design optimal midcourse guidance law with GPM was proposed, the solving process was described in detail, and effectivity of the proposed method was verified with simulation cases. Simulation results show that GPM is dominant in performance index, computation accuracy and computation efficiency, compared with the traditional methods, such as proportional navigation and shooting method, and the computation accuracy and computation efficiency of GPM are determined by the number of collocation nodes. The above all  can provide theoretical reference for research of midcourse guidance law for air-to-air missiles.]]></description>
<pubDate>2013/3/13 9:54:33</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[YANG Xixiang and ZHANG Weihua]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>YANG Xixiang and ZHANG Weihua</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201301006]]></guid><cfi:id>408</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Numerical simulation of heat transfer process in the wall of a high enthalpy and pressure air heater]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201301007]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Three dimensional turbulent fluid flow and heat transfer in the cooling channels of high enthalpy and pressure air heater were numerically investigated. The liquid water was employed as the coolant, and the materials of combustor and nozzle wall were steel and copper respectively, whose thermo physical properties vary with temperature. The hot-fire tests of the facility were performed to validate the simulation results. The influences of gaseous radiation, the channel configuration and cooling routing on the wall heat transfer were discussed and analyzed. The result shows that the heat transfer of combustor wall is affected obviously by the gaseous radiation which has little effect on the nozzle wall. The result will lead to significant error if the gas radiation is neglected. The heat transfer rate of wall is largest if the number and the width of channel was optimized. The flow mode of coolant has a great effect on the coolant side wall temperature but a little impact on the hot-gas side wall temperature.]]></description>
<pubDate>2013/3/13 9:54:33</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[FENG Junhong,SHEN Chibing and ZHAO Fang]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>FENG Junhong,SHEN Chibing and ZHAO Fang</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201301007]]></guid><cfi:id>407</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Depleted shutdown energy management approach for solid launch 
vehicle with singular attitude angle adjustment]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201301008]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Traditional depleted shutdown guidance approaches for solid launch vehicle have excessive attitude angle adjustment times, which lead to the difficulties of the control system design. A depleted shutdown guidance method with singular attitude angle adjustment was proposed. The required apparent velocity was used as a reference, the initial and final values of the rocket attitude angle were chosen by computing the apparent velocity, which is to be consumed. The attitude angle was changed from the initial value to the final value with a constant angle rate, and then the attitude was kept constant till depleted shutdown. The simulation results show that the proposed method with singular attitude angle adjustment satisfies the rocket’s terminal velocity constraint and that the percentage of consumed apparent velocity mode is more than 30%, and the singular attitude angle adjustment strategy can benefit the control system design.]]></description>
<pubDate>2013/3/13 9:54:33</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[YAO Dangnai,ZHANG Li and WANG Zhenguo]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>YAO Dangnai,ZHANG Li and WANG Zhenguo</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201301008]]></guid><cfi:id>406</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[The research on the influence of hypersonic blunt cone pitching 
dynamic derivatives calculation]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201301009]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The steady aerodynamic coefficient and pitching dynamic derivative of blunted conical models in hypersonic flow was validated by using implicit scheme, with the technology of the dual time stepping, rigid rotary grid deformation and least square method. Compared with the results from experiments and engineering method, the influence of the pitching dynamic derivative with different grid, bluntness ratio, angle of attack and the center of the gravity was investigated. Moreover, some of the key differences of the dynamic derivative results were derived from using different schemes, including high-order WENO and WNND schemes. The result shows that the viscid resolution of the scheme is the main source of the difference.]]></description>
<pubDate>2013/3/13 9:54:33</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[ZHAO Wenwen<sup>1</sup>,CHEN Weifang<sup>1</sup>,SHAO Chun<sup>1</sup> and SHI Yuzhong<sup>2</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>ZHAO Wenwen<sup>1</sup>,CHEN Weifang<sup>1</sup>,SHAO Chun<sup>1</sup> and SHI Yuzhong<sup>2</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201301009]]></guid><cfi:id>405</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[A study on “bottleneck” phenomenon during parachute inflation]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201301010]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The inflation process of large-scale or extra large-scale parachute was investigated. The Arbitrary Lagrangian Eulerian (ALE) Method-a Fluid- Structure Interaction (FSI) model, was used to simulate the inflation process of a main parachute (a ringsail parachute, which was used in manned spacecraft) in an infinite mass situation. The dynamic relationship between canopy shape and flow field was obtained, and the adverse inflation phenomena such as asymmetric inflation and whip were observed in simulation results. The “bottleneck” phenomenon in inflation process was found and verified by physical tests. Based on the analysis of calculation results, it is found that the large canopy area, the complicated canopy structure or high inflation speed can block the air mass into the parachute, which can cause the “bottleneck” phenomenon. But the necessary occurrence conditions of the phenomenon need to be studied in future. The present work is significant for explaining parachute working mechanism and preventing its failure.]]></description>
<pubDate>2013/3/13 9:54:33</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[CHENG Han<sup>1</sup>,YU Li<sup>1</sup> and XIA Gang<sup>2</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>CHENG Han<sup>1</sup>,YU Li<sup>1</sup> and XIA Gang<sup>2</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201301010]]></guid><cfi:id>404</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Research on agile satellite dynamic mission 
planning based on multi-agent]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201301011]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Task allocation model based on Multi-Agent theory was established according to mission planning problem of agile satellite after analysis of agile satellites characteristics and satellite multi-user demand. Agile satellite dynamic task re-scheduling model was proposed for the failure of satellite resources in the agile satellite mission planning initial program scheduling. For obtaining the optimal solution we presented agile satellite dynamic task allocation algorithm based on the agreement ending contract net, and designed bidding mechanism, contract net protocols and strategy of biding and assessing biding. Finally, agile satellite mission planning scheduling problem was taken as an example, and satisfactory results were obtained through experiments, which showed that the model was reasonable and the algorithm was efficient.]]></description>
<pubDate>2013/3/13 9:54:33</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[HAO Huicheng,JIANG Wei,LI Yijun and YUAN Ziqing]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>HAO Huicheng,JIANG Wei,LI Yijun and YUAN Ziqing</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201301011]]></guid><cfi:id>403</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Adaptive resampling strategy of sequential optimization
 based on radial basis function surrogate model]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201406004]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Taking account of that it is difficult to obtain the error function to make sequential re-sampling optimization when the predicted error of sampling points in radial basis function(RBF) interpolation surrogate model is zero, the constraint of sampling point distribution was applied in the process of sequential re-sampling. Taking advantage of the convergence performance of potential optimal solution, a re-sampling strategy which is suitable for the sequential optimization of RBF interpolation surrogate model was proposed. The strategy matches the input response property of emulation model with the spatial distribution property of sampling points. Simulation results indicate that the optimization efficiency and precision of the proposed strategy is higher than that of the traditional optimization method based on surrogate model. The optimum point can be well predicted and the number of computational times in primitive model can be reduced obviously by the proposed strategy.]]></description>
<pubDate>2015/1/22 16:38:31</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[WU Zeping,WANG Donghui,YANG Xixiang,JIANG Zhenyu and ZHANG Weihua]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>WU Zeping,WANG Donghui,YANG Xixiang,JIANG Zhenyu and ZHANG Weihua</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201406004]]></guid><cfi:id>402</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Star tracker ground calibration based on
the invariant of interstar angles]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201406009]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[A calibration approach based on the invariant of interstar angles was put forward for star trackers. Compared with common approaches, the sine of interstar angle which provides greater sensitivity for the angle changes closed to 0° was adopted to construct the observation equation instead of its cosine. In the calibration procedure, the two-step approach was proposed to estimate the principal point, focal length, and distortion parameters. The iterative optimization was also proposed to get the optimal estimations. In order to improve the accuracy of calibration, the apparent position of star at the observing time was modified. The experimental results indicate that the sine method is more accurate; and the deviation root-mean-square of the measured interstar angle is 2.2×10<sup>-5</sup> rad after calibrated.]]></description>
<pubDate>2015/1/22 16:38:31</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LIU Haibo<sup>1</sup>,WANG Wenxue<sup>2</sup>,CHEN Shengyi<sup>1</sup>,SU Ang<sup>1</sup> and ZHANG Xiaohu<sup>1</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LIU Haibo<sup>1</sup>,WANG Wenxue<sup>2</sup>,CHEN Shengyi<sup>1</sup>,SU Ang<sup>1</sup> and ZHANG Xiaohu<sup>1</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201406009]]></guid><cfi:id>401</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[An improved differential correction method for trans-lunar 
orbit design]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201406011]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Designing the trans-lunar orbit is one of the key skills for lunar probe mission, and the differential correction is proved to be one of the effective methods to solve a non-linear iteration equation. According to the requirements of high design precision and rapid calculation speed in designing the trans-lunar orbit, a rapid trans-lunar orbit design method from improved differential correction was proposed. Based on the dynamical model, which contains the sun, the earth, the moon, and the earth's J<sub>2</sub> perturbation force in the DE405/LE405 planet and lunar-ephemeris data, the partial derivative matrix of parameters from the perilune to the perigee was deduced. The differential correction matrix was integrated in company with the orbital state variables and velocity, and the transfer orbit design parameters were converged iteratively and rapidly with the precise differential correction matrix. Simulation result shows that the convergence rate of the integral differential correction method is faster than the frequently-used SQP（Sequential Quadratic Programming）method in dynamical models with the same accuracy.]]></description>
<pubDate>2015/1/22 16:38:31</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[HE Boyong,SHEN Hongxin and LI Haiyang]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>HE Boyong,SHEN Hongxin and LI Haiyang</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201406011]]></guid><cfi:id>400</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Analytical downrange prediction of the first entry phase in 
skip entry for lunar module]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201406012]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[For lunar module with low lift to drag ratio, skip entry trajectory must be flown to extend downrange. According to the key element of skip entry trajectory online planning or predictive guidance is how to predict the downrange of the first entry phase rapidly and precisely, an analytical method was proposed. Firstly, closed-form approximate solution of the longitudinal equation of motion was obtained from using matched asymptotic expansion method. Secondly, the first entry trajectory was divided into three phases. In the first phase, altitude served as the independent variable of integration, downrange was obtained from using a composite trapezoidal-rule. In the second and third phases, quadratic polynomial was used for drag-energy profile fitting, and the polynomial coefficients were solved according to the result of the approximate solution, and downrange was obtained by integrating the reciprocal of drag versus energy function. Finally, the accuracy and computational efficiency of the proposed method were analyzed. Simulation results indicate that the characteristic of the proposed method with high accuracy and computational efficiency is very suitable for online planning and guidance.]]></description>
<pubDate>2015/1/22 16:38:31</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[DU Xin,LI Haiyang and HUANG Yuechen]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>DU Xin,LI Haiyang and HUANG Yuechen</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201406012]]></guid><cfi:id>399</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[An investigation on combined entry guidance for lunar 
capsule skip reentry]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201406013]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[A new entry guidance method combined predictor-corrector guidance and reference trajectory guidance was proposed for reducing calculated amount in predictor corrector entry guidance. Predictor-corrector guidance was applied in initial entry phase to improve robustness, and reference trajectory guidance was applied in second entry phase to reduce calculated amount. Through the information of reference trajectory, it was less time consumed in predicting. The method with a new command fast iterative algorithm was designed to reduce the iterative times. The reference command profile was revised according to actual condition of lunar capsule in transfer position so as to compensate error and to improve the quality of the second entry guidance performance. Numerical simulation results demonstrate that the combined entry guidance method is able to lessen time in predicting and fasten correction, and it has the characteristics of high precision and robustness.]]></description>
<pubDate>2015/1/22 16:38:31</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[ZENG Liang,ZHANG Hongbo,ZHENG Wei and LUO Zongfu]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>ZENG Liang,ZHANG Hongbo,ZHENG Wei and LUO Zongfu</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201406013]]></guid><cfi:id>398</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Impact analysis of landing conditions on space capsule’s
impact characteristics]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201406014]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Landing conditions of space capsule have a great effect on impact characteristics. Firstly, the analysis and simulation model of space capsule was established and validated according to an available experimental data. Methods for explicit nonlinear kinetics analysis were used to simulate the landing impact process of space capsule. And the significance effect and the influence disciplines of parameters related to landing conditions on impact characteristics were analyzed by the orthogonal test design. Results demonstrate that the vertical velocity, the pitch angle, the heeling angle and their interactions significantly influence the maximum impact acceleration, while the horizontal velocity and the rolling angle rarely influence it. These conclusions can provide important reference to both the ground tests of landing impact as well as the structural analysis and design.]]></description>
<pubDate>2015/1/22 16:38:31</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[ZHANG Dapeng and LEI Yongjun]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>ZHANG Dapeng and LEI Yongjun</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201406014]]></guid><cfi:id>397</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Ballistic missile burnout states estimation based on exponential 
weighted recursive least square method]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201406015]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Under the early warning of two passive satellite-borne sensors, the exponential weighted recursive least square method was applied to the burnout states estimation of ballistic targets. Due to the weighting factor can characterize the local quasi-linearity of the boost phase trajectory of the target, so to some extent the dilemma that generic polynomial cannot handle the whole boost phase of the target can be overcome. Through a dynamic analysis, the kinematic characteristics of boost phase target along the orientation of vertical surface were explored. On that basis, a novel boost phase motion model is proposed, which is more accurate than traditional planar motion model. Simulation results show that the proposed approach is superior to the traditional ones.]]></description>
<pubDate>2015/1/22 16:38:32</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[CHAI Hua,LIANG Yangang and TANG Guojin]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>CHAI Hua,LIANG Yangang and TANG Guojin</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201406015]]></guid><cfi:id>396</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Uncertainty analysis of the rocket trail cover separation]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201406016]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[To assess the risk of the rocket trail cover separation movement, the multi-body dynamic model in separation process was established according to the Kane's equation, and the collision checking model based on the relative location estimation of the key point-collision boundary was built. The Monte Carlo method and the Morris screening method were used to analysis the uncertainty of the separation process when the input parameters had random deviations. The dispersion characteristics of the separation motion state were got from the Monte Carlo method and the sensitivity of each parameter was ranked by using the Morris screening method. Results show that the trail cover separation solutions possess high reliability, which can satisfy the security requirements in the case of the input parameters with deviations. Among all the input parameters, wind interference and the thrust deviation of the thruster from ejection pistons has greatly influenced the distance of drop points, and the horizontal distance between the rocket and the trail cover has been greatly affected by the wind and the out canister velocity under the circumstances of ignition.]]></description>
<pubDate>2015/1/22 16:38:32</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[JIA Ruyan,WANG Tao,JIANG Zhenyu,HU Fan and ZHANG Weihua]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>JIA Ruyan,WANG Tao,JIANG Zhenyu,HU Fan and ZHANG Weihua</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201406016]]></guid><cfi:id>395</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Study of ignition process of boron particles in relatively static atmosphere]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201406017]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The ignition process of boron particles in relatively static atmosphere was studied systemically. In view of the gas flow around the boron particle, the heat and mass transfer process between the boron particle and the surroundings, a one dimensional ignition model of boron particles was proposed. The changing regularities of important parameters of the gas and the particle in the two typical cases, namely, the successful ignition case and the degenerate ignition case were studied. And the mechanisms for them were analyzed in detail. The result shows that Stefan flow in both typical cases will undergo changing flow direction. Stefan flow undergoes flowing to the particle surface from the gas, and then it flows to the gas from the particle surface. Study of ignition process of boron particles in the paper shows that ignition time decrease with consideration of Stefan flow at the particle surface. And the effect increases with the ambient pressure.]]></description>
<pubDate>2015/1/22 16:38:32</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[FANG Chuanbo<sup>1</sup>,XIA Zhixun<sup>1</sup>,HU Jianxin<sup>2</sup> and XIAO Yunlei<sup>1</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>FANG Chuanbo<sup>1</sup>,XIA Zhixun<sup>1</sup>,HU Jianxin<sup>2</sup> and XIAO Yunlei<sup>1</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201406017]]></guid><cfi:id>394</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Trajectory combinatorial optimization design for airborne 
time sensitive guided bombs in extended range period]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201406018]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In order to improve the gliding ability in mid-course trajectory of the aerial time-sensitive guided bombs, a combinatorial optimization design method which can be applied to the extended-range project of aerial time-sensitive guided bombs was proposed by combining the minimum principle with the adaptive evolutionary particle swarm algorithm. In the base of the model of mass-centre motion in longitudinal plane, performance index function and inequality constraint functions were derived. Hamilton equation was established by introducing Lagrange multiplier vectors to convert the unconstrained functional extremum problem and deduce the satisfactory optimization model which gave consideration to all optimization object functions. By means of the adaptive evolutionary particle swarm algorithm, double design variables, attack angle and wing gears, of extended trajectory were optimized combinatorially. The simulation results indicate that the range of the guided bombs controlled by double variables is obviously more than that of bombs controlled by single variable as long as the constraint condition of state equation is satisfied. The optimization results have reference value for trajectory design of guided bombs.]]></description>
<pubDate>2015/1/22 16:38:32</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[BAI Hongyang<sup>1,2</sup>,LI Weiming<sup>3</sup>,SUN Ruisheng<sup>1</sup> and XIONG Shuwang<sup>1</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>BAI Hongyang<sup>1,2</sup>,LI Weiming<sup>3</sup>,SUN Ruisheng<sup>1</sup> and XIONG Shuwang<sup>1</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201406018]]></guid><cfi:id>393</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Oscillation suppression strategy during tether-tugging reorbiting]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201406029]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The dynamic equations of system centroid orbit and tether oscillation were established. And the dynamic characteristics of tether oscillation without tether control and the effects of tether control on tether oscillation were analyzed. An expect rate of tether which suppress tether oscillation was constructed and tether tension control law was designed. Simulation results indicate that when there is no tether control, tether oscillation is in periodic reciprocating motion around the equilibrium position. The tether tension control is continuous and smooth, which makes tether actual length keep well track of the expected length, and the tether oscillation is suppressed effectively at the same time.]]></description>
<pubDate>2015/1/22 16:38:32</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LIU Haitao,ZHANG Qingbin,YANG Leping and ZHU Yanwei]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LIU Haitao,ZHANG Qingbin,YANG Leping and ZHU Yanwei</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201406029]]></guid><cfi:id>392</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Stiffness analysis of bolted flange joint based on 
parameterized modeling]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201406031]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In order to analyze the effects of geometric parameters on the stiffness of bolted flange joint, a parameterized model of bolted flange joint was constructed by using PCL (Patran Command Language) on the platform of software MSC.Patran. The law of the stiffness of bolted flange joint with the change of geometric parameters was studied, and the sensitivity of geometric parameters was analyzed based on the parameterized model. The results show that the ratio of the location of hole is the most sensitive factor to the stiffness of bolted flange joint, and the next one is thickness of upper flange. When the length of upper body is up to a const, the stiffness of bolted flange joint is insensitive to the length of upper body, and this conclusion can provide a reference to simplify the dynamic model of joint.]]></description>
<pubDate>2015/1/22 16:38:33</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[JIANG Guoqing,LI Jiawen and TANG Guojin]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>JIANG Guoqing,LI Jiawen and TANG Guojin</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201406031]]></guid><cfi:id>391</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Design of the network protocol of a wireless 
spacecraft high speed data network]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201405001]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Wireless spacecraft data networks can unburden the wire problems of the spacecraft, which makes it a promising technology for spacecraft light miniaturization. To replace the peer-to-peer three-wire Low Voltage Differential Signaling cables in spacecrafts, design of a wireless spacecraft high speed data network based on Impulse Radio Ultra Wideband was proposed. The wireless communication protocol referring to the American military data bus standard MIL-STD-1553B protocol was described in detail. The communication protocol adopted the time division command response mechanism, and its physical layer, data link layer, network layer and application layer were designed to meet the requirements of the wireless spacecraft high speed data communication. The design of a demonstration of the spacecraft high speed data network was tested and verified. It is proved that the system bit error rate is less than 1010<sup>-9</sup>. The design of the protocol IP core is flexible, reliable and scalable. ]]></description>
<pubDate>2014/11/25 10:16:01</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[ZHOU Li<sup>1,2</sup>,AN Junshe<sup>1</sup>,XIE Yifang<sup>1</sup>,XIONG Weiming<sup>1</sup> and XUE Changbin<sup>1</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>ZHOU Li<sup>1,2</sup>,AN Junshe<sup>1</sup>,XIE Yifang<sup>1</sup>,XIONG Weiming<sup>1</sup> and XUE Changbin<sup>1</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201405001]]></guid><cfi:id>390</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Bank-to-turn autopilot design for morphing aerial bombs based on 
discrete-time sliding mode control]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201405002]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In order to improve the robust performances of Bank-to-turn control system within the morphing phase, a Bank-to-turn autopilot design for the morphing aerial bombs based on the discrete-time sliding mode control principle was proposed. The Bank-to-turn control affine system was modeled. Meanwhile, aiming at the time-varying and coupling characteristics, input-output feedback linearization was utilized to decouple the system into three independent discrete-time subsystems. The aerodynamic coefficient deviation items caused by sampling errors of the sweepback were regarded as the external uncertain disturbances, and a discrete-time sliding mode Bank-to-turn autopilot for the morphing aerial bombs was designed. The simulation results indicate that the discrete-time control system has a good robust performance for the time-varying parametric perturbations engendered by wings morphing and can realize the decoupling control among channels. The tracking delay and errors are related to the sampling period, therefore, the actual hardware performances and command tracking accuracy should be considered in selecting sampling period.]]></description>
<pubDate>2014/11/25 10:16:01</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[BAI Hongyang<sup>1</sup>,LI Weiming<sup>1,2</sup>,XIONG Shuwang<sup>1</sup> and SUN Ruisheng<sup>1</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>BAI Hongyang<sup>1</sup>,LI Weiming<sup>1,2</sup>,XIONG Shuwang<sup>1</sup> and SUN Ruisheng<sup>1</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201405002]]></guid><cfi:id>389</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Investigation of cluster bomb projection  aerodynamic problem 
using overset grid method]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201405003]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Cluster bomb projection is a typical multi-body aerodynamic problem with relative motions, and is also a valuable application area for the overset grid method. The MI-GRID overset software, the fluid dynamic governing equation and the rigid body movement equations were employed to investigate the aerodynamic trajectory and movement characteristics in bomb separation process. The orthogonal experimental design was also employed to discuss even to assess the effect of the initial and aerodynamic interference on bomb separation movement. Results indicate that the bomb in projection flow field is greatly affected gesture motions by the shock interference. When a singular bomb is projected, the shock of the missile makes the pitching movement of the bomb vary abruptly. While the multiple bombs are projected, the reflection shock that is extracted by the bomb makes the bomb rise, which can affect the bomb bay's flowing.]]></description>
<pubDate>2014/11/25 10:16:01</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[ZHANG Hairui<sup>1，2</sup>,YUAN Wu<sup>2</sup>,FAN Jingjing<sup>2</sup> and ZHANG Weihua<sup>1</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>ZHANG Hairui<sup>1，2</sup>,YUAN Wu<sup>2</sup>,FAN Jingjing<sup>2</sup> and ZHANG Weihua<sup>1</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201405003]]></guid><cfi:id>388</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Comparison of high-precision finite volume method and 
discontinuous Galerkin method]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201405006]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The high-precision finite volume method (FVM) and discontinuous Galerkin method (DGM) were compared in different test cases through numerical examples. Results show that:with the same precision, the calculation error of DGM is obviously less than that of FVM; DGM's reconstruction process is comparatively simpler than FVM's, but its computational time is much longer since its freedom-degree of polynomial solution is higher under the condition of high order and it needs to calculate volume points. Decreasing the freedom-degree numbers of polynomial solution in the time evolution process is an essential method for high-precision calculation in the reality applications.]]></description>
<pubDate>2014/11/25 10:16:01</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[FAN Jinzhi and LI Hua]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>FAN Jinzhi and LI Hua</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201405006]]></guid><cfi:id>387</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Optimal excitation trajectories for spacecraft’s moment of inertia 
parameters on-orbit estimation]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201405007]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[On the basis of matrix analytical theory, the identifiability of inertial moment parameters was studied. A linear regression model in term of the unknown parameters was derived from attitude dynamics equations; the condition number of regression matrix was defined as the quantitative index of identifiability degree; taking the maximum of identifiability degree as objective function, an optimal control model was built. The pseudospectral optimal control was employed to solve the command trajectory of control moment gyro and to improve the identification precision and convergence velocity. The method of dual-unscented Kalman filter identified parameters under simulated circumstances. Results demonstrate that the optimal excitation design can improve the performance of parameter's identification and has high robustness to inaccurate priori information.]]></description>
<pubDate>2014/11/25 10:16:01</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[YANG Yajun,LIAO Ying and LIU Xiangchun]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>YANG Yajun,LIAO Ying and LIU Xiangchun</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201405007]]></guid><cfi:id>386</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Spray characteristic of gas-liquid double swirl coaxial injector]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201405009]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The volume of fluid method was used to analyze the flow process in pressure swirl injector. SLR camera and phase doppler anemometry were used to measure the spray characteristics of swirl injector and gas-liquid double swirl coaxial injector. Results show that the total pressure loss occurs mainly in inlet section, convergent section, and columned section of swirler trough. The longer the columned section is, the thicker the liquid film and the smaller the spray cone angle is. The range of spay particle distribution increases gradually along the radial direction while the axial velocity distribution decreases firstly and then increases along radial direction. Spray characteristic of gas-liquid double swirl coaxial injector is greatly influenced by gas-liquid ratio (GLR). While GLR is small enough, swirling air increases the spray cone angle and decreases the range of particle distribution; while GLR is large enough, the expansion of air compresses the spray, pushing large droplets to the center of the spray. And at the edge of spray locates small droplets from second atomization.]]></description>
<pubDate>2014/11/25 10:16:01</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[KANG Zhongtao<sup>1，2</sup>,LI Qinglian<sup>1，2</sup>,ZHANG Xinqiao<sup>1，2</sup> and CHENG Peng<sup>1，2</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>KANG Zhongtao<sup>1，2</sup>,LI Qinglian<sup>1，2</sup>,ZHANG Xinqiao<sup>1，2</sup> and CHENG Peng<sup>1，2</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201405009]]></guid><cfi:id>385</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Error analysis of dynamic testing table of inertial measurement unit and its increment 
motion compensation]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201405010]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In order to implement high accurate and large dynamic test tasks of inertia measurement unit (IMU), 6-degrees of freedom electric dynamic test table of IMU was designed on the basis of Gough-Stewart platform. Error model was established and the effect of electric cylinder length error on the accuracy of the system was analyzed. The passive spiral increment motion of electric cylinder produced in the movement of IMU dynamic test table was analyzed further and the compensation algorithm of the movement was studied. The quantitative analysis of the error brought from the passive spiral increment motion shows that the effect of the motion to the pose accuracy of dynamic test table is significant. In order to clear the effect, the compensation algorithm was accomplished and was applied to the real-time control system of the dynamic test table of IMU. Experimental results show that the position accuracy of dynamic test table of IMU reaches the design specification due to compensation algorithm.]]></description>
<pubDate>2014/11/25 10:16:02</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[CAI Hong<sup>1</sup>,SUN Wenli<sup>1</sup> and MA Jianming<sup>2</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>CAI Hong<sup>1</sup>,SUN Wenli<sup>1</sup> and MA Jianming<sup>2</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201405010]]></guid><cfi:id>384</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Numerical simulation on effect of velocity ratio on gas/gas injector 
combustion performance]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201405011]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In order to investigate the combustion flow field of gas/gas injector in full-flow staged combustion cycle engine, the flowing combustion processes of different velocity ratios between fuels and oxidants were numerically simulated by solving the Navier-Stokes equations. Simulation results which agree well with the experimental results show that: the combustion efficiency increases and the combustion flame surface advances along with the increase of velocity ratio; if the length of the engine is restricted, the effective combustion can be achieved by increasing the velocity ratio appropriately.]]></description>
<pubDate>2014/11/25 10:16:02</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[YUAN Lei and SHEN Chibing]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>YUAN Lei and SHEN Chibing</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201405011]]></guid><cfi:id>383</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Spline filtering algorithm based on interacting multiple model for 
line-of-sight rate estimation in strap-down seeker system]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201405012]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[A spline filtering algorithm based on interacting multiple model algorithm (IMM-SF) was proposed to estimate Line-of-sight (LOS) rate in strap-down seeker system. Based on the mapping relation between body LOS and inertial LOS, the inertial LOS angles were obtained and used as virtual observed data of filters. A set of process noise models were set up, and every model worked independently based on the spline filter. The valuation output of IMM-SF was the weighted composition of the valuation outputs of all parallel spline filters. By using this method, the unknown maneuver models of the target were no longer indispensable, which makes the method more convenient to use. Process noise could be adaptively adjusted under the configuration of IMM. The Monte-Carlo simulation results show that the LOS rate can be estimated effectively based on SF-IMM, which can also improve the accuracy of estimation.]]></description>
<pubDate>2014/11/25 10:16:02</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LIANG Yangang,HAO Daoliang and TANG Guojin]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LIANG Yangang,HAO Daoliang and TANG Guojin</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201405012]]></guid><cfi:id>382</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Data exchange method for solid body field coupling based on 
compactly supported radial basis function]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201405013]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[According to the data interpolation problems of non-matched meshes in the simulation calculation of thermal-electric solid body field, a interpolation algorithm based on compactly supported radial basis function was proposed. The transfer matrix   was derived and the calculation program used for data exchange between two non-matched meshes based on compactly supported radial basis function was developed. An example of several groups of temperature interpolation between two non-matched meshes was verified, and the influence of different parameters on calculation time and precision was analyzed. The result shows that the algorithm is efficient and accurate for data exchange calculation of solid body field coupling non matched meshes, especially for thermal-electric coupling interpolation.]]></description>
<pubDate>2014/11/25 10:16:02</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[HUO Lin<sup>1</sup>,YANG Tao<sup>1</sup> and CHENG Xinghua<sup>2</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>HUO Lin<sup>1</sup>,YANG Tao<sup>1</sup> and CHENG Xinghua<sup>2</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201405013]]></guid><cfi:id>381</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Time-triggered Ethernet for space utilization]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201405020]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Ethernet for space utilization added time-triggered protocol to a star topology network that was used for Ethernet service; moreover it was fully compatible with the standard IEEE802.3. This Ethernet can effectively solve the problems of real-time, uncertainty and reliability on communications for payload communicating through standard Ethernet. Time-triggered Ethernet was based on global reference time, and the real-time data transmission kept strict timing, supported time and event-triggered communication simultaneously. Time-triggered channel in this Ethernet was suitable for real-time synchronous or periodic message transmission, while event-triggered channel was suitable for sporadic or aperiodic message transmission. To prove the result that Ethernet can ensure the network reliability and security, enhance flexibility, and can greatly improve network availability, many work have to be done. For example, it designed an Ethernet topology and protocol stack for space utilization, described system communication process, studied time-triggered protocol, and simulated synchronization and network performance.]]></description>
<pubDate>2014/11/25 10:16:02</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[QIU Aihua<sup>1,2</sup>,ZHANG Tao<sup>1</sup> and GU Yidong<sup>1</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>QIU Aihua<sup>1,2</sup>,ZHANG Tao<sup>1</sup> and GU Yidong<sup>1</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201405020]]></guid><cfi:id>380</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Optimization study of heat transfer properties for generic shingle 
ceramic thermal protection system]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201405024]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[For the demand of hypersonic aircraft for generic shingle ceramic thermal protection system (TPS), the transient heat transfer model of TPS structure was established and the influences of some factors, such as material properties, thickness, phase change materials and its location, on heat transfer properties were investigated. Results show that: material properties and thickness of heat insulation layer play a key role in heat transfer properties, while these of the heat protection layer almost exist no effect; the introduction of phase change materials obviously improves the heat transfer properties of TPS structure; the location optimization of phase change layer is an effective method to improve the heat transfer properties and reduce the thickness; the thickness optimization of heat insulation layer can provide reference for the TPS design. ]]></description>
<pubDate>2014/11/25 10:16:03</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LI Guangde,ZHANG Changrui,HU Haifeng and ZHANG Yudi]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LI Guangde,ZHANG Changrui,HU Haifeng and ZHANG Yudi</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201405024]]></guid><cfi:id>379</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Equivalent crack analysis method of the cylindrical shell 
with prefabricated defects]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201405026]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Focusing on the problem that the traditional finite element analysis results of the cylindrical shell with prefabricated defects couldn't be applied on the engineering practice effectively due to the low computing precision of stress and strain, an equivalent crack analysis method with high redundancy was proposed. Treat the prefabricated defects as typical crack, and analyze the crack stability with the singular crack element method, then assess the structural integrity of the cylindrical shell with prefabricated defects according to the analytical results of the crack stability. The analysis result obtained through this new method is more reliable than the traditional finite element method, and it is practical in promoting the safety margin of the engineering design, especially for the prefabricated defects of cylindrical shell structure working in severe environment with high risk coefficient like linear explosive separation device of the missile.]]></description>
<pubDate>2014/11/25 10:16:03</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[SHEN Zhibin and ZHANG Weixing]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>SHEN Zhibin and ZHANG Weixing</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201405026]]></guid><cfi:id>378</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[A method for space reconnaissance task relevant degree 
analysis and redundancy deletion]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201405030]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[To solve the problem of redundant tasks in space reconnaissance demand, a method for space reconnaissance task relevant degree analysis was proposed, considering the sources of demand, requirements of quality, time preference and spatial range. The relevant elements of space reconnaissance were analyzed, and calculation method of task relevant degree was given based on these four elements. A specific algorithm to reduce probability of redundancy tasks was proposed with task relevant degree. An algorithm of redundancy analysis was considered in the case of accurate priority, justice and hybrid. An example was given to illustrate the effectiveness of this method. The results show that the method has good versatility, which can effectively support space reconnaissance missions preprocessing.]]></description>
<pubDate>2014/11/25 10:16:03</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LI Zhimeng,LIU Gang and TAN Qun]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LI Zhimeng,LIU Gang and TAN Qun</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201405030]]></guid><cfi:id>377</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Multiobjective optimization design of isolator for spacecraft]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201404001]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[It is common to use passive isolator to protect the payload from the platform noise in space applications. The design of a passive isolator involves a trade-off between the resonant peak reduction and the high frequency attenuation. Firstly, the equation of motion and transfer function model for single-stage and two-stage connector model was derived, and then the multiobjective optimization model, in which the objective functions are the resonant peak reduction and the high frequency attenuation, was proposed,. Secondly, the multiobjective optimization design method for the design of the passive isolator was proposed, using the multiobjective evolutionary algorithm based on decomposition (MOEA/D). The simulation result shows that the proposed method is effective for the design process of the passive isolator, and can provide multiple candidate solutions for the designer.]]></description>
<pubDate>2014/9/4 17:19:43</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LUO Jun<sup>1,2</sup> and TANG Guojin<sup>1</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LUO Jun<sup>1,2</sup> and TANG Guojin<sup>1</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201404001]]></guid><cfi:id>376</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Effects of electrodes configuration on the performance 
of pulsed plasma thrusters]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201404002]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The electrode is one of the most important components of the pulsed plasma thruster(PPT), which has great influence on PPT performance. In view of this, the upper limitation of PPT efficiency theoretically was analyzed, and the results showed that the upper limitation of PPT efficiency increases by increasing the flare angle or decreasing the end width of electrodes. And then the impulse bit and the mass bit of different PPTs were measured by varying the flare angle and the end width of electrodes. The experimental results indicated that the flare angle has different effects on mass bit of PPTs for different electrode shapes; effects of flare angle on impulse bit are similar to the effects of flare angle on mass bit for corresponding electrode; the specific impulse increases firstly and then decreases with the increase of flare angle; the influence of electrode shape on the performance of PPTs is different at different flare angles.]]></description>
<pubDate>2014/9/4 17:19:43</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[ZHANG Hua,WU Jianjun,HE Zhen,ZHANG Daixian and LU Gaofei]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>ZHANG Hua,WU Jianjun,HE Zhen,ZHANG Daixian and LU Gaofei</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201404002]]></guid><cfi:id>375</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[The  flow hysteresis in the supersonic curved channel]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201404003]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[With the centerline Mach-number distributions provided in advance, a two-dimensional supersonic wave-cancelled channel was designed by the Method of Characteristics. The shock train，wall static pressure distributions and separation region were investigated. The relationship between the shock train and back pressure was also investigated. The flow-field had dual solutions when the head of the shock train was in the vicinity of the channel inflection. When the flow evolved into the single-solution domain from the dual-solution domain，the larger separated zone transferred quickly and the shock-train structure evolved fast.]]></description>
<pubDate>2014/9/4 17:19:43</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[GUO Shanguang,WANG Zhenguo and ZHAO Yuxin]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>GUO Shanguang,WANG Zhenguo and ZHAO Yuxin</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201404003]]></guid><cfi:id>374</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[An anti-rendezvous evasion maneuver method 
based on degree of observability]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201404004]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[An anti-rendezvous evasion maneuver method is proposed in order to escape from the spacecraft that has autonomous approaching ability. Supposing that a two impulse C-W navigation strategy is used by the approaching spacecraft, first a bearing-only relative navigation model is built. Then, a definition of degree of observability based on state estimation error is proposed so as to quantify observability. By using the degree of observability conception, the evasion maneuver direction is chosen as its gradient, which guarantees that every unit impulse can reduce the system observability mostly. Finally, the numerical simulation is conducted with different maneuver impulse, and the result shows that the method proposed can attenuate the system observability obviously. The method offers a new viewpoint for evasion maneuver research.]]></description>
<pubDate>2014/9/4 17:19:43</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[YU Dateng<sup>1</sup>,WANG Hua<sup>1</sup> and LI Jiuren<sup>2</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>YU Dateng<sup>1</sup>,WANG Hua<sup>1</sup> and LI Jiuren<sup>2</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201404004]]></guid><cfi:id>373</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Analysis of seismic response and seismic-relieving 
design of a launch vehicle]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201404006]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[For a launch vehicle in erect status, an earthquake may bring severe consequence, such as the toppling failure of the launch vehicle. To ensure the safety of a launch vehicle during earthquake, analysis of earthquake time history response was executed. The distributions of peak moment and peak displacement in longitudinal direction of the launch vehicle were derived. Frequency-domain characteristic of moment response in key positions were researched. Seismic-relieving design was performed on the launch vehicle. Seismic response's influence disciplines of link stiffness between rocket and launcher, stiffness of isolation bearing were analyzed. The results show that: (1) the maximum of moment response occurs in tail of the launch vehicle, and the maximum of displacement response occurs in front of the launch vehicle; (2) the seismic response can be reduced significantly by changing link stiffness between rocket and launcher or equipping the launcher with isolation bearing.]]></description>
<pubDate>2014/9/4 17:19:44</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LIU Caizhi<sup>1,2</sup> and TANG Guojin<sup>1</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LIU Caizhi<sup>1,2</sup> and TANG Guojin<sup>1</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201404006]]></guid><cfi:id>372</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[The  gliding phase guidance for hypersonic gliding vehicle 
based on improved MPSP]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201404007]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Aiming at the reentry guidance of hypersonic gliding vehicle considering multi-constraints, the research proposes an improved predictor-corrector guidance law, which is based on model predictive static programming(MPSP). The initial value generator was founded by using the rapid generation of three dimensional trajectory, which solves the MPSP problem of providing guess history difficultly and refreshing nominal trajectory for the initial perturbation. The kinematic model of the hypersonic gliding vehicle was built based on energy, and the predictor-corrector guidance based on MPSP was deduced. The influence factors from the initial decent phase to the gliding phase were investigated. The digital simulation was carried out in gliding phase considering perturbations of the initial values and aerodynamic parameters. The results turn out that the improved MPSP predictor corrector method have the advantages of precise initial guess values, computational efficiency and strong robustness to the perturbations.]]></description>
<pubDate>2014/9/4 17:19:44</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[GUO Haifeng,HUANG Changqiang,DING Dali and XIAO Hong]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>GUO Haifeng,HUANG Changqiang,DING Dali and XIAO Hong</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201404007]]></guid><cfi:id>371</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Numerical study for the effects of ablation and pyrolysis
on the hypersonic reentry flow]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201404008]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Through numerically simulating the hypersonic reentry flow with ablation of carbon-phenolic heat-shield, the effects of ablation and pyrolysis on the thermochemical properties and electron densities of the flowfield were analyzed. 19 chemical species were considered and a two-temperature model was taken to describe the thermal nonequilibrium. The Navier-Stokes equations of thermochemical nonequilibrium flow coupled with the ablating boundary condition were solved to obtain the steady-state solution of the flowfiled. The effects of ablation were shown in comparison with the non-ablating baseline case, which has a non-reacting, non-catalytic wall and equilibrium radiation wall temperature. The method to determine surface chemical composition of the pyrolysis gas was discussed, and the effects of the pyrolysis ratio were investigated. The simulation and analysis performed on RAM-C model at flight speed of 7.65km/s and altitude of 61km or 71km show that, the dominant ablation and pyrolysis species are CO, H<sub>2</sub> and H, and both the ablation species and the effects of ablation are limited to the boundary layer. The mass fractions of atoms and ions decline as a result of ablation and this may result in the decrease of the peak values of electron density when they appear in the boundary layer. Furthermore, the ablation effects become more pronounced as the pyrolysis ratio rises, and the effects extend further into the flowfield with increasing distance from the stagnation point or with higher flight altitude.]]></description>
<pubDate>2014/9/4 17:19:44</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[ZHANG Wei,ZENG Ming,XIAO Lingfei and XU Dan]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>ZHANG Wei,ZENG Ming,XIAO Lingfei and XU Dan</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201404008]]></guid><cfi:id>370</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Applying the analytic solution of pressure 
discontinuity to modify the AUSM<sup>+</sup>-up scheme]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201403001]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[AUSM<sup>+</sup>-up  scheme is one of the most important schemes of ASUM-family. By introducing pressure dissipative mechanism into the convective fluxes and velocity diffusion into pressure fluxes, the convergence and robustness are remarkably improved in all Mach number regimes. However, based on an analysis of the scheme, it is found that a nonphysical phenomenon of infinite mass flux emerges when the Mach number is zero. For conquering the imperfection, the analytic solution of pressure discontinuity is obtained by the characteristic method. According to the results, the item of pressure dissipation is modified, and a new AUSM<sup>+</sup>-up scheme is developed. Using the new scheme, the strong discontinuity problems of shock wave, pressure discontinuity and shock wave diffraction are simulated. The Calculation results fit the theory results well.]]></description>
<pubDate>2014/7/17 17:22:22</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LI Gan,CHENG Mousen and LI Xiaokang]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LI Gan,CHENG Mousen and LI Xiaokang</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201403001]]></guid><cfi:id>369</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Central WENO hybrid schemes used in the finite-volume method]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201403002]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The Central-WENO hybrid schemes (CWENO6 schemes) are developed based on the theory analysis. While the CWENO6 schemes were used in the finite volume method, the 3 order MUSCL deconvolution method was used instead of the origin 5 order WENO deconvolution method to reduce the deconvolution computation cost. According to the numerical test, it is found that the CWENO6 schemes have more powerful ability to represent the details of the flow filed because of its low numerical dissipation comparing to the WENO5 schemes under the same computation mesh. Finally, it is concluded that the CWENO6 schemes are an efficient method for the simulation of multi-dimension complex flow using finite volume method.]]></description>
<pubDate>2014/7/17 17:22:22</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[FAN Jinzhi and LI Hua]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>FAN Jinzhi and LI Hua</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201403002]]></guid><cfi:id>368</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Reflection of p-wave at free surface of thermal elastic saturated porous medium]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201403003]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Based on the diffusion equation of prorous-thermoelastic waves presented by the authors, the problem of reflection of plane p-wave on a free interface was investigated and the expressions of the reflection coefficient were derived. Then, the effect of thermal expansion coefficient of the porothermoelasticity on the propagation speed of p<sub>1</sub> in the medium was discussed firstly. Furthermore, through the analysis of the effect frequency, incidence angle on the amplitude characteristics of reflection wave, the drainage and no drainage conditions were considered, , and the effect of interfacial pervious and impervious conditions was also discussed. It is shown that the thermal physical parameters have a certain effect on the propagation of thermoelastic waves, and such parameters as frequency, incidence angle and surface drainage conditions are factors greatly affecting the reflection amplitude of two types of compression wave, shear wave and thermal wave.]]></description>
<pubDate>2014/7/17 17:22:22</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[ZHENG Rongyue<sup>1,2</sup>,LIU Ganbin<sup>2</sup> and TANG Guojin<sup>1</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>ZHENG Rongyue<sup>1,2</sup>,LIU Ganbin<sup>2</sup> and TANG Guojin<sup>1</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201403003]]></guid><cfi:id>367</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Aerodynamic characteristics of the twist fin vehicle]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201403004]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In order to study the influence of aerodynamic characteristics on the twist fin vehicle, twist rate and average attack angle was introduced to represent geometric features of tail. By solving the N-S equations in standing state in rotating frame, a numerical simulation of the aerodynamic characteristics of cruciform layout twist fin vehicle was made . The results show that the twist fin can increase the rolling moment and balancing speed of aircraft and the balancing speed is proportional to the twist rate. When the twist rate increases, the twist fin’s initial resistance coefficient increases. When the balancing speed is reached, the resistance coefficient will decrease. In the critical twist rate, increased with the twist rate, the wing surface pressure distribution will be improved effectively at the balancing speed. The research results have reference value for the aerodynamic configuration design stability design of vehicle.]]></description>
<pubDate>2014/7/17 17:22:22</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[ZHAO Bobo<sup>1,2</sup>,LIU Rongzhong<sup>1</sup>,GUO Rui<sup>1</sup>,YUAN Jun<sup>1</sup> and ZHANG Jun<sup>1</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>ZHAO Bobo<sup>1,2</sup>,LIU Rongzhong<sup>1</sup>,GUO Rui<sup>1</sup>,YUAN Jun<sup>1</sup> and ZHANG Jun<sup>1</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201403004]]></guid><cfi:id>366</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[A new multiscale simulation method for primary atomization]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201403005]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[A new multiscale method of primary atomization is proposed. The liquid blobs larger than the grid volumes were captured by the volume of fluid algorithm, the droplets comparable with the grid volumes or smaller were simplified to particles and tracked by a Lagrangian particle tracking model on a virtual mesh. Large eddy simulation with one equation sub-grid scale turbulent energy transport model was used to describe the turbulent flow. A new developed code was validated by several cases, and some key parameters were investigated to improve the precision. The primary atomization of a single jet was calculated, and the results of instantaneous and average characteristics are in good agreement with the experimental results.]]></description>
<pubDate>2014/7/17 17:22:22</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LIU Changbo<sup>1</sup>,LEI Fanpei<sup>2</sup> and ZHOU Lixin<sup>1</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LIU Changbo<sup>1</sup>,LEI Fanpei<sup>2</sup> and ZHOU Lixin<sup>1</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201403005]]></guid><cfi:id>365</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Using local tone mapping to match multi-sensor images]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201403006]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Tone mapping is an efficient image matching algorithm adaptive to brightness and contrast variation. Due to the complex and nonconforming relation between multi-sensor images, tone mapping can hardly be directly used on multi-sensor images to achieve satisfactory results. To improve the matching rate, the local tone mapping algorithm is proposed, which includes the following steps: Firstly, the template map is divided into nonoverlapping blocks., Then, each block is processed through histogram equalization and weak slice transform. Next, the distance maps are calculated for every block by local tone mapping. Finally, the matching result is obtained by fusion all these distance maps. Experimental results show that, the matching rate of local tone mapping significantly outperforms tone mapping and mutual information, while its computation time is slightly longer than that of the tone mapping and less than that of the mutual information.]]></description>
<pubDate>2014/7/17 17:22:22</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LI Zhuang<sup>1,2</sup>,TU Guoyong<sup>2</sup>,LI Weijian<sup>2</sup> and ZHANG Hongliang<sup>1</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LI Zhuang<sup>1,2</sup>,TU Guoyong<sup>2</sup>,LI Weijian<sup>2</sup> and ZHANG Hongliang<sup>1</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201403006]]></guid><cfi:id>364</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Modeling and simulation analysis of detection probability 
for space-based AIS]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201403010]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Aiming at solving the low detection probability problem of space-based AIS, the received signal collision phenomenon and ship detection probability model were studied. The difference between Space-based AIS and traditional terrestrial AIS was compared and analyzed. And the new technical challenge of space-based AIS was pointed out. The problem of AIS signals collision from multi SOTDMA cells was studied in detail. The detection probability model based on ship density function was established theoretically. The effects of slot collision, orbit height, antenna swath and Class B ships on detection probability were estimated quantitatively by simulations, which can provide theoretical reference for designing and evaluating the space based AIS in the future.]]></description>
<pubDate>2014/7/17 17:22:22</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[CHENG Yun,CHEN Lihu and CHEN Xiaoqian]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>CHENG Yun,CHEN Lihu and CHEN Xiaoqian</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201403010]]></guid><cfi:id>363</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Applying the  improved genetic algorithm to optimize the oribit 
for space-based optics surveillance platform]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201403011]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Aiming at the effects of space objects visibility constraints including the Earth masking, the Earth shadow, the sunlight, the Moon light and the relative angle velocity between space object and platform, the sun-synchronous twilight circularity orbit was selected and the improved multi-mutation adaptive genetic algorithm was adopt to solve the single platform orbit inclination angle optimization based on Two-line Elements (TLE) of catalog objects. Simulation results show that the improved multi-mutation adaptive genetic algorithm can effectively solve the optimum individual while the multi-mutation adaptive genetic algorithm may not. In addition, it is found that the calculation capacity can be improved with a magnitude in equivalent performance using about 10% random selected objects.]]></description>
<pubDate>2014/7/17 17:22:23</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LIU Xiangchun,LIAO Ying and WEN Yuanlan]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LIU Xiangchun,LIAO Ying and WEN Yuanlan</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201403011]]></guid><cfi:id>362</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Vision-based satellite position measurement]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201403012]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Satellite orbit measurement based on ground station, such as USB and VLBI, is restricted in its observation arcs. In addition, the long distance of deep space explorer mission forms a new challenge to current satellite TT&C system. If the satellite can estimate its position by its own CCD camera, the time and distance constraints will be eliminated. With a view of this, a vision-based position estimation method for satellite was proposed. It registered satellite image with a reference image and then estimated the satellite’s position according to photogrammetry. An experiment using the image, orbit data of space mission was conducted. By mutually verifying the vision method and the traditional method, it illustrates the effectiveness and accuracy. Our vision-based position estimation method is a good complement to the traditional method; it can save work of ground observation stations and have a promising application prospect in deep space exploration.]]></description>
<pubDate>2014/7/17 0:00:00</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LI Xiang<sup>1,2</sup>,ZHU Zunshang<sup>1,2</sup>,BU Yanlong<sup>3</sup> and SHANG Yang<sup>1,2</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LI Xiang<sup>1,2</sup>,ZHU Zunshang<sup>1,2</sup>,BU Yanlong<sup>3</sup> and SHANG Yang<sup>1,2</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201403012]]></guid><cfi:id>361</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[GPS/DR integrated navigation aided by simultaneous 
localization and mapping]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201403014]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Considering the performance of Global Positioning System (GPS)/Dead Reckoning (DR) integrated system degrading dramatically when GPS signal is outage or blocked, a Compressed Extend Kalman Filter (CEKF) based Simultaneous Localization and Mapping (SLAM) aided GPS/ DR integrated navigation method was addressed. The error of DR system was restrained with SLAM correction when the GPS solutions were unavailable. Accordingly, the GPS location corrected the error and improves the uncertainty of SLAM mapping when GPS positioning was accessible. A filter of CEKF based SLAM/GPS integrated was designed to realize the real time implement of SLAM/GPS in a large scale environment. Compared with the SLAM locating using the real experiment dataset, the SLAM aided GPS/DR integrated method enhanced the system performance of positioning as well as the accuracy of SLAM mapping raised approximate 10m.]]></description>
<pubDate>2014/7/17 17:22:23</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[CHENG Jiantong,ZHANG Weihua and JIANG Zhenyu]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>CHENG Jiantong,ZHANG Weihua and JIANG Zhenyu</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201403014]]></guid><cfi:id>360</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Method of guidance handover in midcourse guidance phase 
of air-to-air missile about cooperative multi-platform]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201403015]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Aiming at solving the problem of target information break in the process of handing over the guidance of Mid-Long range air-to-air missile between the same kinds of aircrafts in cooperative air combat, a method of “virtual target” was proposed: the virtual target approached the real target gradually, when the aspect angle of missile-virtual target and the missile-real target matched, and the process of handing over the guidance was over. Three different modes of approaching movement was proposed, and the affection on the over loading of air-to-air missile was analyzed through simulation of the situation of the target in the process of maneuvering and not maneuvering. The simulation results showed that handing over the guidance appropriately and moderately can transform the break information which is unmanageable into the break information which is manageable, and can avoid the information breaking into improper value if the guidance is handed over roughly.]]></description>
<pubDate>2014/7/17 17:22:23</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[DIAO Xinghua,FANG Yangwang,ZHANG Lei,GAO Xiang and MAO Donghui]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>DIAO Xinghua,FANG Yangwang,ZHANG Lei,GAO Xiang and MAO Donghui</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201403015]]></guid><cfi:id>359</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[IDRP: An interplanetary DTN routing protocol]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201403017]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[A novel interplanetary DTN routing protocol (IDRP) is designed to provide a general networking solution over interplanetary network scenarios. IDRP enables DTN nodes to estimate the recovery time to its neighbor nodes using the historical connection information. When two DTN nodes in the same region contact each other, they exchange their estimations to decide whether to use each other as a relay. For storage resource is constraint in deep space nodes, IDRP also takes storage consumption into consideration. Simulations based on NS2 were conducted in a Mars-to- Earth scenario. A modified epidemic routing strategy and an only-gateway-selected routing strategy are used as contrast. The simulation results show that IDRP achieves 14% higher delivery ratio and 50% less average transmission delay than the other two strategies, as well as better storage utilization.]]></description>
<pubDate>2014/7/17 17:22:23</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[YU Yang<sup>1,2</sup> and CHEN Xiaomin<sup>1</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>YU Yang<sup>1,2</sup> and CHEN Xiaomin<sup>1</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201403017]]></guid><cfi:id>358</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Combined method of impulse maneuver detection based on 
observation innovation and system state information]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201403029]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Aimed at the problem that maneuver detection delay causes the uncertainty of tracking maneuvering target, a combined detection method (χ<sup>2</sup> -β) was proposed for tracking maneuvering spacecraft with impulse power. By using Observation Innovation and α-βmaneuver dynamics model, the method detected the impulse maneuver to track maneuvering satellite. Through simulation and analysis, a comparison between the χ<sup>2</sup> detection method with β detection method was made. It proves that the sensitivity of χ<sup>2</sup> detection to maneuvering frontier correlate with the sampling points and motor threshold. The combined detection method does not incur much computation and,is superior to the traditional method, thus it has practicality in satellite engineering.]]></description>
<pubDate>2014/7/17 17:22:24</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[HUANG Pu,QIAN Shan and LI Hengnian]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>HUANG Pu,QIAN Shan and LI Hengnian</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201403029]]></guid><cfi:id>357</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Relaxation effects of reflection of SV waves at surface of 
saturated porous thermoelasticity]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201402001]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Based on the Biot’s wave theory and thermoelastic theory for saturated porous medium, three relaxation factors were introduced and the generalized thermoelastic theory for saturated porous medium was developed. Reflection of SV waves on the surface of the plane was used to analyze the influence of relaxation effect on the reflection, and the expressions of the reflection coefficient for the p<sub>1</sub> wave, p<sub>2</sub> wave, T-wave and S-wave were derived. Numerical results were obtained and used to discuss the difference of reflection amplitude for four kinds of reflection waves among the generalized thermoelastic theory G-TE, L-S theory, and G-L theory. The effect of the relaxation time factors was also discussed. It is indicated that there is apparent effect of G-TE, L-S theory, and G-L theory on the results and it is different from p<sub>1</sub> wave,p<sub>2</sub> wave and S-wave. In addition, there is greater effect of relaxation time on p<sub>2</sub> wave, and less effect on p<sub>1</sub> wave, and the effect can be omitted on the S wave.]]></description>
<pubDate>2014/5/14 17:10:47</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[ZHENG Rongyue<sup>1,2</sup>, LIU Ganbin<sup>2</sup>, TANG Guojin<sup>1</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>ZHENG Rongyue<sup>1,2</sup>, LIU Ganbin<sup>2</sup>, TANG Guojin<sup>1</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201402001]]></guid><cfi:id>356</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Numerical simulation of separation of central stage 
and booster stage for a carrier rocket]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201402002]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The dynamic overset method and Eulerian approach were applied to solve the unsteady NS function and 6DOF movement function, and to numerically simulate the separation processes of KSR-III rocket’s core and to booster with and without additional forces. Major factors that affect the separation processes were also analyzed. It shows that the numerical results agree with the experimental results, indicating that the dynamic overset assembly method is able to correctly predict the complex flow between the rocket’s core and booster. Furthermore, based on the results of numerical simulations, separation parameters and rules of the booster under different conditions are also obtained.]]></description>
<pubDate>2014/5/14 17:10:47</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[ZHANG Hairui<sup>1,2</sup>, FAN Jingjing<sup>2</sup>, ZHANG Weihua<sup>1</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>ZHANG Hairui<sup>1,2</sup>, FAN Jingjing<sup>2</sup>, ZHANG Weihua<sup>1</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201402002]]></guid><cfi:id>355</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Design of an asteroid flying-by mission for CHANG’E-2]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201402003]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[An asteroid rendezvous plan for CHANG′E-2 was put forward and the corresponding mission was designed to maximize the satellite utilization. First, the satellite status of CHANG′E-2 at present was introduced. Based on the constraint of the current CHANG′E-2 orbit and remaining fuel and TT&C (telemetry, track, and command) capacity, the design of optimal transfer trajectory and the selection of rendezvous asteroid were studied. The suitable asteroids for rendezvous were given as a result. Second, the mid-course correction was studied according to two orbit maneuver modes, i.e., the fixed interval mode and the fixed interval mode with a least velocity increment constraint. Finally, the TT&C condition of the asteroid rendezvous mission was briefly analyzed according to the Chinese deep space network. The results show that the fuel remains can support the rendezvous of CHANG′E-2 with Asteroid 1997XF<sub>11</sub> and 2005VS. Furthermore, the Chinese deep space network can provide an 8-h daily VLBI (Very Long Baseline Interferometry) tracking at least in the interplanetary course. The velocity increment for mid-course corrections is less than 10 m/s.]]></description>
<pubDate>2014/5/14 17:10:47</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LIU Lei<sup>1,2</sup>, WU Weiren<sup>3</sup>, TANG Geshi<sup>1,2</sup>, ZHOU Jianliang<sup>2</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LIU Lei<sup>1,2</sup>, WU Weiren<sup>3</sup>, TANG Geshi<sup>1,2</sup>, ZHOU Jianliang<sup>2</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201402003]]></guid><cfi:id>354</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[A nonlinear covariance analysis method for space station rendezvous 
phasing based on unscented transformation]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201402004]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[As for the long-time error propagation problem of the space station rendezvous phasing，a nonlinear covariance analysis method based on the unscented transformation (UTCAM) is presented. The strategy of rendezvous phasing and the computation method of orbit maneuver parameters is proposed，then the principles and flow of UTCAM are introduced. The comparison between UTCAM and the two methods of STK and the  Monte-Carlo shows that the relative error of covariance analysis between those methods is under 1.2%, and the computation consumption time is only 1/460 that of Monte-Carlo, so it can accomplish the propagation of mean and covariance rapidly and exactly for nonlinear systems. Finally, the error propagation of a 20-day rendezvous phasing of space station is conducted by using UTCAM, and the results are validated by the Monte-Carlo simulation.]]></description>
<pubDate>2014/5/14 17:10:47</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[HUANG Haibing, ZHANG Jin]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>HUANG Haibing, ZHANG Jin</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201402004]]></guid><cfi:id>353</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Diving guidance with maneuver based on feedback 
linearization and slide mode control]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201402005]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The slide mode tracking guidance strategy for hypersonic vehicle that can realize both precise guidance and maneuver flight was investigated. First, the diving trajectory which can satisfy terminal constraints in longitudinal direction and the maneuvering trajectory were designed. Second, with the aid of feedback linearization, the nonlinear motion equations were converted into the linear ones, which can be used to track the designed trajectories. Besides, in order to improve the guidance performance, slide mode tracking guidance law was proposed and the law was converted into nonlinear system to get nonlinear slide mode tracking guidance law. The guidance law is formed from the current motion states completely, therefore, the relative motion information can be decreased enormously. Finally, the results of a CAV-H vehicle guidance test show that the algorithm can realize maneuver flight and high precision guidance under the path constraints even if the outside disturbances exist. Therefore, it can offer references for precision guidance and maneuver penetration for hypersonic vehicle in dive phase.]]></description>
<pubDate>2014/5/14 17:10:47</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[ZHU Jianwen<sup>1</sup>, LIU Luhua<sup>1</sup>, TANG Guojian<sup>1</sup>, BAO Weimin<sup>1,2</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>ZHU Jianwen<sup>1</sup>, LIU Luhua<sup>1</sup>, TANG Guojian<sup>1</sup>, BAO Weimin<sup>1,2</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201402005]]></guid><cfi:id>352</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Numerical simulation of the impacts of block modes on 
the flow field of isolator]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201402006]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The design of a blockage adjustor at the exit is commonly used in simulating the impacts of backward pressure on the isolator flow field. Numerical simulation was adopted to study the effects of different block modes. Three modes were compared, including installing a flat on the ramp side wall, a flat on the cowl side wall and a wedge in the middle of the flow field. The results show that due to the asymmetric boundary layer on the ramp wall and cowl wall, the shock trains formed by them are all next to the cowl side. The intensity of the shock train generated by the second mode is stronger and the boundary layer separates more evidently, which chocks the isolator more easily and poses difficulty for the study of shock train in experiment. The other two modes can generate similar flow field, but the first one can be realized more easily. ]]></description>
<pubDate>2014/5/14 17:10:47</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[CHEN Zhi, YI Shihe, WU Yu, QUAN Pengcheng]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>CHEN Zhi, YI Shihe, WU Yu, QUAN Pengcheng</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201402006]]></guid><cfi:id>351</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Configuration optimization design of hypersonic 
gliding lifting body]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201402007]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The hypersonic vehicle has a large number of configuration parameters, and its aerodynamic shape design is very complicated. To overcome this difficulty, a lifting body shape parametric design method is proposed. This method is based on class function/shape function transformation (CST) and power function expression, whose design variables are limited to six ones, which makes it very convenient for configuration analysis and design. By means of orthogonal experiment analysis, the influence of the configuration parameters on volume efficiency and lift-drag ratio of the lifting body was studied, and the ones with the great influence were obtained. Meanwhile, the experiment results found that the configuration parameters have conflict influence on the volume efficiency and lift-drag ratio. Thus, to search for the best configuration parameters, a Kriging surrogate model based multi-objective genetic algorithm was applied to design the lifting body shape, in which the volume efficiency and lift-drag ratio were taken as the two conflict objectives under the constraints of the longitudinal stability and vehicle volume. Numerical results show the efficiency of the method and a uniform Pareto front was obtained. The volume efficiency and lift-drag ratio of the typical optimized shape can be increased by 17.31% and 11.94%, respectively, in comparison with the baseline. Differences of the results gained from the Kriging surrogate model and real physical model are less than 4%. Furthermore, the influences of leading edge blunting on aerodynamic character were researched. The results indicate that, the lift-drag ratio of the lifting body decreases significantly with the increase of blunting radius. It is also found that the optimized results can be extrapolated to the leading edge blunting shapes when aerodynamic character is the unique concern.]]></description>
<pubDate>2014/5/14 17:10:47</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[MA Yang, YANG Tao, ZHANG Qingbin]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>MA Yang, YANG Tao, ZHANG Qingbin</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201402007]]></guid><cfi:id>350</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Vibration reduction of payloads on spacecraft based on structure 
parameters of spacecraft-bracket system]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201402008]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The dynamical interaction of payload brackets and spacecraft frame structure can observably magnify the responses of payloads. Vibration reduction studies usually focus on component-level payload brackets, but in this research, spacecraft frame structure and payload brackets are considered as a whole system (Spacecraft-Bracket System). A certain spacecraft was modeled with finite element method. With structure parameters extracted from this model, a system-level lumped parameter model was built, and the univariate analysis for structure parameters was done. The results indicate that the lumped parameter model can expose the coupling pattern of payload brackets and spacecraft frame structure clearly, and that the sensitivity for responses of payloads related to frequency parameters of both structures are evidently higher than that related to damp and mass parameters. Consequently, for improving the dynamic environment of payloads, the frequency relationship of payload brackets and spacecraft frame structure should be anatomized in spacecraft structure design stage.]]></description>
<pubDate>2014/5/14 17:10:47</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[ZHU Shiyao, LEI Yongjun]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>ZHU Shiyao, LEI Yongjun</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201402008]]></guid><cfi:id>349</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Study and implementation of sounding-rocket picture capture 
and compression system]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201402009]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[As is required by sounding rocket utilization, a real-time multi-channel picture capture and compression system applied in sounding rocket is studied and realized in the study, which introduces two key techniques applied in the system. The system bases its architecture on ARM and FPGA, and adopts a dedicated video-compression chip as the core processing unit. By way of improving the reliability of time division multiplexing of cameras and optimizing the control schemes of compression ratio, the system satisfies the requirement of low power consumption and high compression ratio in sounding rockets. It has compact circuit framework, high integration level and great flexibility. Practical tests show that, the system has some good features, such as being light-small, low-power, and low-cost. In the experiment named Space Environment Vertical Exploration, the system shot important scenes, including the separation of rocket head and engine, as well as the deployment of electric field detection boom. By adoption of contour volume evaluation methods, it is concluded that the pictures shot during the flight have sufficient definition for scientific research and engineer application.]]></description>
<pubDate>2014/5/14 17:10:47</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[CHEN Ping<sup>1,2</sup>, WANG Linlin<sup>1</sup>, CHEN Zhimin<sup>1</sup>, JIANG Xiujie<sup>1</sup>, XIONG Weiming<sup>1</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>CHEN Ping<sup>1,2</sup>, WANG Linlin<sup>1</sup>, CHEN Zhimin<sup>1</sup>, JIANG Xiujie<sup>1</sup>, XIONG Weiming<sup>1</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201402009]]></guid><cfi:id>348</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Perturbation compensation strategy for MEO non-resonant 
navigation constellation maintenance]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201402010]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Global navigation constellation maintenance is an important problem. Firstly, the model of MEO constellation formation was advanced. Then, with consideration of main perturbation forces and orbit ephemeris error, the constellation formation evolvement law was analyzed and asserted with some satellites orbital data. Also, anti-perturbation compensation strategy was put forward, an improved decoupling control method was proposed, and the effect of satellite launch time on anti-perturbation compensation strategy was discussed and analyzed. Finally, some key results were concluded as a summary, which will be helpful for the design of the global navigation constellation with inertial space and its maintenance and control strategies for its rotation around the earth.]]></description>
<pubDate>2014/5/14 17:10:47</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[QIAN Shan, LI Hengnian, WU Shenggang]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>QIAN Shan, LI Hengnian, WU Shenggang</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201402010]]></guid><cfi:id>347</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Differential flatness based trajectory planning for 
hypersonic glide vehicle]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201402011]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[For the trajectory planning problem in hypersonic glide vehicle, a differential flatness based three-degree-of-freedom trajectory generation approach is proposed. Based on the flatness analysis of the simplified longitudinal motion model, the reference longitudinal trajectory planning problem was mapped into the flat output space to improve the solving efficiency by eliminating the dynamical constraints and reducing the design dimension. Then the initial problem was transformed into a nonlinear programming problem utilizing global polynomial approximations to the flat outputs. To compensate for the effects of the earth rotation and external disturbances, a Proportion-Differentiation control based reference trajectory tracking controller was designed with good convergence capability. By integrating the lateral motion determined by the error corridor of heading angle based bank angle revision, the three-degree-of-freedom gliding trajectory was ultimately generated. Numerical simulations were conducted to validate the feasibility and effectiveness of the approach presented here.]]></description>
<pubDate>2014/5/14 17:10:48</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[CAI Weiwei, YANG Leping, LIU Xinjian, ZHU Yanwei]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>CAI Weiwei, YANG Leping, LIU Xinjian, ZHU Yanwei</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201402011]]></guid><cfi:id>346</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[An improved approach for positioning of ground-based pseudolite 
navigation system based-on receiver’s clock error restriction]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201402012]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[When the ground-based pseudolite navigation system is used for vehicle, there will be some bad geometric configuration situations because of the area restriction for pseudolites. If the traditional single positioning algorithm is used with pseudo range only as usual, the precision of positioning for vehicles will be low. In light of this, this study proposed that the inaccurate solution of receiver’s clock error affects the precision of positioning to a great extent. For this situation, an improved approach was suggested to obtain a better precision of positioning through increasing the accurateness of solution of receiver’s clock error. The main idea was to obtain the observation model of the receiver’s clock error and then adding the model to the positioning equations. The simulation results indicate that the approach is feasible and effective.]]></description>
<pubDate>2014/5/14 17:10:48</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LYU Hanfeng, ZHANG Liang, WU Jie]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LYU Hanfeng, ZHANG Liang, WU Jie</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201402012]]></guid><cfi:id>345</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Experimental investigation on injection characteristics of assembled 
transverse injectors in supersonic crossflow]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201402013]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The injection, mixing and atomization characteristics of transverse liquid jet in liquid-fueled scramjet are the determining factors for the efficiency of the combustion chamber. An origin image analysis method, without any threshold choosing section, was developed in house to get the unique unstable boundary of the transverse jet without any manual effects. The lateral extension boundary capturing method, which is based on PIV technique and the corresponding image analysis method, was developed to illustrate the lateral outer boundary of the jets. Results from targeted and comparative experiments indicate that, compared with the single jet case, the penetration heights and lateral extension become larger in the assemble jets cases. A larger distance between the streamwise assembled double injectors contributes to a higher penetration height of the jet.]]></description>
<pubDate>2014/5/14 17:10:48</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[TONG Yiheng<sup>1,2</sup>, LI Qinglian<sup>1,2</sup>, WU Liyin<sup>1,2</sup>, LI Chun<sup>1,2</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>TONG Yiheng<sup>1,2</sup>, LI Qinglian<sup>1,2</sup>, WU Liyin<sup>1,2</sup>, LI Chun<sup>1,2</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201402013]]></guid><cfi:id>344</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[A capture initial information solution method for ISLs of navigation 
constellation based on ephemeris-aided method]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201402015]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In view of the large dynamic and fast acquisition requirement of inter-satellite links (ISLs) signal, a capture initial information solution method is presented for ISLs of navigation constellation. This method evaluates time-delay and Doppler frequency based on ephemeris. The analysis shows that this method has a simple realization process, a high speed of restraining and a high precision of evaluation, and can achieve the degree of nanosecond for the time delay through merely two times of iteration, which has greatly reduced the computing difficulty and complexity. This analysis is made upon the model of BeiDou navigation system and can provide reference for our country’s ISLs design.]]></description>
<pubDate>2014/5/14 0:00:00</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LI Xianbin, WANG Yueke, CHEN Jianyun]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LI Xianbin, WANG Yueke, CHEN Jianyun</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201402015]]></guid><cfi:id>343</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Rendezvous control of spacecraft formation based on 
cyclic pursuit algorithm]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201401001]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Rendezvous control of spacecraft formation based on cyclic pursuit algorithm is researched. The mathematical model of cyclic pursuit algorithm was established and deduced, and a new control law for spacecraft formation rendezvous was proposed, in which planar cyclic pursuit algorithm and normal proportional derivative method were combined. A rendezvous control for a formation by three spacecrafts adopting linear and nonlinear cyclic pursuit algorithm respectively is simulated. Simulation results show that, the proposed control law based on cyclic pursuit can meet the rendezvous requirement of spacecraft, spacecrafts rendezvous at the reference center determined by their initial position along clockwise trajectories, changing process of relative distance and relative velocity between them is consistent, and consumption of velocity gain is lesser. All this can provide theoretical reference for research of formation control for spacecrafts.]]></description>
<pubDate>2014/3/12 14:49:30</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[YANG Xixiang,YANG Tao and ZHANG Weihua]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>YANG Xixiang,YANG Tao and ZHANG Weihua</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201401001]]></guid><cfi:id>342</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Heterogeneous parallel compressible flow solver based on MPI+CUDA]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201401002]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[A compressible flow heterogeneous parallel solver based on MPI+CUDA on CPU/GPU heterogeneous system was established. Then different parallel computing models and optimizing methods of compressible flow parallel computing algorithm were discussed. This solver runs different codes with difference resources: the codes which are complex or have low computing density are run on CPU, while the codes which are simple or have high computing density are run on GPU. The heterogeneous systems’ computing results and the efficiencies with homogeneous systems were compared through several problems. Finally, the heterogeneous algorithm was applied to the hypersonic flow. The result shows that the algorithm is robust and the computing efficiency is improved ten times more than that of the homogeneous algorithm.]]></description>
<pubDate>2014/3/12 14:49:30</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LIU Feng<sup>1,2</sup>,LI Hua<sup>1</sup>,TIAN Zhengyu<sup>1</sup> and PAN Sha<sup>1</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LIU Feng<sup>1,2</sup>,LI Hua<sup>1</sup>,TIAN Zhengyu<sup>1</sup> and PAN Sha<sup>1</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201401002]]></guid><cfi:id>341</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Research on guidance law with multiple constraints of 
hypersonic vehicle for cruise phase]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201401003]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The equilibrium condition of hypersonic vehicle during cruise phase is modeled, under which the vehicle can maintain constant speed and altitude. It analyzed the equilibrium conditions that the vehicle can satisfy. Based on the conditions, a guidance law with multiple constraints and terminal course angular constraint is proposed, and the analytic solution is concluded. The method is adaptive since the guidance command is obtained through the analytic expressions in real time. In the end, simulations under different deviations have proved the method is effective.]]></description>
<pubDate>2014/3/12 14:49:30</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[WAN Yujun,CHEN Kejun,LIU Luhua and WU Jie]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>WAN Yujun,CHEN Kejun,LIU Luhua and WU Jie</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201401003]]></guid><cfi:id>340</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[A velocity and height estimation method based on vision/inertial 
for aircraft in unknown environments]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201401004]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[For aircraft navigation in unknown environments, a velocity and height estimation method based on vision/inertial integrated navigation is proposed. An extended inertial navigation state equation was formulated, which contains several aircraft’s positions at latest several imaging times, and a linear vision measurement equation based on two view epipolar geometry constraints was adapted to correct inertial velocity error using a Kalman filter. And then, the coordinates of ground features were estimated by the stereo vision method, which was used to estimate the height of the aircraft. Simulation has been implemented by using the typical cruise trajectory of the aircraft, and the result shows that our method works well for correcting the velocity and height errors, which enables the velocity and height not to drift with time. As a result, it can also suppress the position error of the aircraft.]]></description>
<pubDate>2014/3/12 14:49:30</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[SU Ang<sup>1,2</sup>,LEI Zhihui<sup>1,2</sup>,ZHANG Yueqiang<sup>1,2</sup>,ZHU Xianwei<sup>1,2</sup> and LIU Haibo<sup>1,2</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>SU Ang<sup>1,2</sup>,LEI Zhihui<sup>1,2</sup>,ZHANG Yueqiang<sup>1,2</sup>,ZHU Xianwei<sup>1,2</sup> and LIU Haibo<sup>1,2</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201401004]]></guid><cfi:id>339</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Optimal guidance for terminal phase of approaching observation]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201401005]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Approaching observation is a new way of space-based inspection. Precisely steering the flight vehicle to the observing point near the target is one of the key technologies. An optimal terminal guidance is presented for the terminal approaching. Firstly, the process of approaching observation is transformed to an optimal control problem by founding equations of relative motion in inertial coordinate systems and performance index which synthesizes the fight time and fuel consuming. Then optimal thrust direction, nozzle working hours, and time-to-go are derived, based on which a scheme of optimal guidance is designed. Finally, simulations are conducted and results demonstrate that the guidance algorithm can meet the requirements of approaching observation mission with the high precision. The study herein also is helpful to deep space exploration, rendezvous and docking.]]></description>
<pubDate>2014/3/12 14:49:31</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LI Guanghua,ZHANG Hongbo and TANG Guojian]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LI Guanghua,ZHANG Hongbo and TANG Guojian</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201401005]]></guid><cfi:id>338</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Characteristic analysis of disturbance aroused 
by solar array tracking drive]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201401006]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The disturbance, aroused by sun-tracking drive of solar array, has become one of the major barriers for improving the performance of high-precision spacecraft. With the aim to obtain the regular characteristics of this disturbance, the solar array and the drive assembly were considered as a couping system and an electromechanical integration model and a dynamic simulation program are presented based on the major aspects of main driving steps and the Simulink software platform.. The correctness was verified by comparing the experiment results, and the effects of solar array rigid-flexible coupling and the centroid bias to disturbance characteristics were analyzed. The results indicate that the rotation speed fluctuation can activate low order torsion modes of solar array, and disturbance spectrums include both frequency characteristics of motor driving and structure vibration, but torsion vibration has little effect on rotation angle. The centroid bias of solar array can motivate translational-rotational coupling vibration, activate out-of-plane bending modes, change the distribution of disturbance spectrum, and increase the amplitude of disturbance.]]></description>
<pubDate>2014/3/12 14:49:31</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[ZHU Shiyao,XIE Yan and LEI Yongjun]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>ZHU Shiyao,XIE Yan and LEI Yongjun</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201401006]]></guid><cfi:id>337</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[The equivalence prove of least-square solutions for 
two single point positioning models]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201401007]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[For the least-square solutions of two positioning models in single-point position, the equivalence proving of position estimation and its precision is given. The basic positioning model and single-difference positioning model were described respectively, then the single-difference positioning model was arranged into three cases, and the least-square solution of each case was proved equal to that of basic positioning model. Finally, the equivalence of the two models was proved by processing the experiment data, and the efficiency of least-square arithmetic for the two models was compared with each other.]]></description>
<pubDate>2014/3/12 14:49:31</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LV Hanfeng,WU Jie and ZHANG Liang]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LV Hanfeng,WU Jie and ZHANG Liang</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201401007]]></guid><cfi:id>336</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[A low-thrust trajectory optimization method based on 
motion synthesis]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201401008]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[A novel method based on motion synthesis is proposed for low-thrust trajectory design and optimization. Firstly, the representation of the low-thrust trajectory was obtained by using the motion synthesis technique. In this representation, the equations of motion was decomposed into three independent motions and the analytical expressions of the three motions were deduced separately. Then the approximate analytical expression of the low-thrust trajectory was obtained by synthesizing of the three motions. Secondly, based on this representation, the original problem was converted into a nonlinear programming problem. Finally, the method was applied to three rendezvous missions: from the Earth to the asteroid 1989ML, to the Mars, and to the Venus respectively. It is shown that the transfer orbits satisfy the mission constraints. Numeral results fully validate the availability and the high efficiency of the method.]]></description>
<pubDate>2014/3/12 14:49:31</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[JIANG Xiaoyong,ZHANG Hongbo and TANG Guojian]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>JIANG Xiaoyong,ZHANG Hongbo and TANG Guojian</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201401008]]></guid><cfi:id>335</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[A  burn-coast-burn-coast  deorbit guidance approach based on 
energy and angular momentum indices]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201401009]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The problem of “burn-coast-burn-coast” deorbit trajectory guidance with finite thrust is studied. The entry interface conditions are transformed into indices of energy and angular momentum, based on which the critical geocentric distance of “burn-coast” deorbit problem is derived and the relationship between entry interface conditions and deorbit strategy is analyzed. Then, the relative changing law of energy and the angular momentum of spacecraft in the burn arc are derived, and the guidance equation is derived by the idea that the energy and angular momentum decrease synchronously in the same relatively rate. According to the entry interface conditions, the trajectory is supposed to be a “burn-coast-burn-coast” style. The first burn needs no guidance, and the direction of the thrust is opposite to the velocity direction. The second burn uses the guidance law. Simulations of different altitude and different entry interface conditions are implemented. The results indicate that the method can effectively solve the deorbit guidance problem that the single “burn-coast” method fails, and the computational effort is not large.]]></description>
<pubDate>2014/3/12 14:49:31</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[ZOU Yi,ZHANG Hongbo and TANG Guojian]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>ZOU Yi,ZHANG Hongbo and TANG Guojian</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201401009]]></guid><cfi:id>334</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[An improved ephemeris algorithm of 
Beidou GEO satellite for user]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201401015]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The orbital inclination of 5°coordinate rotation is required in the GEO ephemeris algorithm for users. Aimed at this step, an improved method that the BeiDou GEO satellite position is calculated directly by using the classical broadcast ephemeris algorithm for user was presented, and meanwhile the corresponding broadcast ephemeris fitting algorithm based on the second class of non singularity orbit elements was given. In this method, the classical orbit elements were replaced by the second class of non-singular orbit elements, which solves the problem that the coefficient matrix is non-positive in the process of the classical broadcast ephemeris fitting algorithm because of the small inclination angle. This avoids the orbital inclination of 5°coordinate rotation process, decreases the calculating steps time and enhances the GEO ephemeris algorithmic efficiency. The simulation results show that the accuracy of the improved method is as much as the original algorithm in the satellite orbit fitting process and is reduced slightly in the satellite orbit extrapolation process. But it can still meet the requirement of navigation and position for users. Finally, the validity of the improved algorithm is verified by using orbital data of the actual BeDou GEO broadcast ephemeris.
〖WTHZ〗Key words： 〖WTBZ〗BeiDou satellite navigation system; GEO satellite; broadcast ephemeris fitting; the second class of non singularity orbit elements]]></description>
<pubDate>2014/3/12 14:49:31</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[XIE Xiaogang,ZENG Dazhi,LONG Teng and ZHANG Lei]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>XIE Xiaogang,ZENG Dazhi,LONG Teng and ZHANG Lei</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201401015]]></guid><cfi:id>333</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Neural network predictive guidance method based on 
pattern of optimal guidance]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201401024]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In order to solve the contradiction between high guidance accuracy and fast real-time solving in traditional predictive guidance method, a neural network predictive guidance method is presented, based on the pattern of optimal guidance. The method predicts trajectory based on high believable simulation of kinematic aircraft model, and uses optimization theory to iterative solution of guide variable, so as to generate off-line sample data. By means of choosing multi-modal neural network, training neural network based on dispatching management, to complete the design of the neural network prediction guidance controller. CAV as an example to design, results show that: The method is less real time calculation, fast real-time solution and high guidance accuracy, of which the comprehensive performance is far better than the traditional predictive guidance method.]]></description>
<pubDate>2014/3/12 14:49:32</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[ZENG Qinghua,DONG Ronghua and PI Shuwu]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>ZENG Qinghua,DONG Ronghua and PI Shuwu</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201401024]]></guid><cfi:id>332</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Simulation on the performance of linear throttleable sonic nozzle]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201506011]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The mode transition of combined-cycle engine makes it necessary to throttle the mass flow rate of propellants continuously and stably. Aiming at gaseous propellant, a throttleable sonic nozzle was designed on the basis of normal sonic nozzle. The throttleable sonic nozzle achieves continuous throttling through a plug moving along axis. By adopting the twice-envelope method, the contour of the plug was designed to satisfy the linear characteristic of mass flow rate. Performances of the throttleable sonic nozzle were investigated through the numerical simulation of computational fluid dynamics. It is found that the mass flow rate is independent under the back pressure when the back pressure is lower than the critical back pressure and the critical back pressure ratio increases as mass flow rate decreases. The linear relationship between mass flow rate of linear throttleable sonic nozzle and location of plug was verified and results show that the discharge coefficient is high and hardly be affected by the location of plug.]]></description>
<pubDate>2015/12/31 10:11:13</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[CHENG Peng, LI Qinglian, ZHANG Xinqiao, KANG Zhongtao and CHEN Huiyuan]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>CHENG Peng, LI Qinglian, ZHANG Xinqiao, KANG Zhongtao and CHEN Huiyuan</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201506011]]></guid><cfi:id>331</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Space station attitude maneuver method considering partial fault of single gimbal control moment gyroscopes]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201506012]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The fault character of pyramid configuration single gimbal control moment gyroscopes (SGCMG) was analyzed. The calculation approach solving the replanned attitude maneuver path was proposed based on the Legendre pseudo spectral method. Considering the unpredictability of the SGCMG fault, an adaptive steering law was designed. Using this steering law, the fault state of SGCMG was detected and the parameters of the steering law was self-tuned. The simulation results reveal that, the large angle attitude maneuver can be accomplished by using the path replanned method and the adaptive steering law, when the SGCMG encounter partial fault. The proposed method can cope with the partial fault state of the SGCMG during attitude maneuver effectively, thus improving the security and reliability of the space station attitude maneuver mission.]]></description>
<pubDate>2015/12/31 10:11:14</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[ZHAO Qian and TANG Guojin]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>ZHAO Qian and TANG Guojin</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201506012]]></guid><cfi:id>330</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Mixed moment validation metric for models with multivariate output]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201506013]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Considering the relations among multi-outputs and the mean of single output, the mathematical expectation of single dimensional variable and covariance metric of multi-dimensional variables were introduced into the validation metrics for models. The new metrics of LA-3M and LR-3M were proposed for validating multi-responses at a single validation site, while the metrics of GA-3M and GR3M were proposed to collect data of multiple responses observed at multiple validation sites. These metrics were examined  through a numerical test case and an engineering example to illustrate their feasibility and effectiveness. Results show that the proposed metrics are efficient and they can easily measure the differential degree of multiple responses between calculation model and physical experiment.]]></description>
<pubDate>2015/12/31 10:11:15</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[ZHAO Lufeng<sup>1</sup>, LYU Zhenzhou<sup>1</sup>, ZHANG Leigang<sup>2</sup> and WANG Xinwei<sup>3</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>ZHAO Lufeng<sup>1</sup>, LYU Zhenzhou<sup>1</sup>, ZHANG Leigang<sup>2</sup> and WANG Xinwei<sup>3</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201506013]]></guid><cfi:id>329</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Dynamics modeling and simulation of water-exit course of small submarine-launched missile under wave disturbance]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201506018]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Based on Morison equation, a dynamics model of water-exit missile under wave disturbance was built, which takes the coupling between wave and motion of missile into account. The water-exit motion of small submarine-launched missile was simulated and analyzed. The effects of coupling between wave and motion of missile body to wave disturbance, illustrated by change process of attitude of missile, were studied. The influences of sea condition, wave phase, velocity and attitude of missile to the motion of water-exit course were analyzed. The result indicates that the characteristics of submarine-launched, which are small in size and fast in water-exit, reduce the impact of wave to attitude of missile. In addition, the wave disturbance to high-speed water-exit missile is significantly affected by sea condition, duration of water-exit course and wave phase. The dynamic model which takes the coupling between wave and motion of missile into account is more accurate.]]></description>
<pubDate>2015/12/31 0:00:00</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[ZHANG Chongxian]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>ZHANG Chongxian</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201506018]]></guid><cfi:id>328</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Analysis of influential factors to supercooling phenomenon during ascent stage of stratospheric long duration balloons]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201505014]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Supercooling phenomenon of stratospheric long duration balloons means that the temperature of helium gas inside is lower than that of atmosphere outside, this will cause the loss of buoyancy and affect ascent process of the balloon as a result. Radiation and convection thermal models and the vertical dynamic model of long duration balloons were established, and the influence regularity of some important factors, including initial net buoyancy, skin thermal physical parameters, launch time and launch date, on supercooling phenomenon was analyzed. Simulation results show that the temperature difference between helium gas and outside atmosphere enlarges remarkably along with the increase of initial net buoyancy, and the temperature difference decreases when the absorptivity for visible light and infrared radiation increases. Simulation results also show that the influence of launch time and launch date on supercooling phenomenon is much smaller, while flight time from ground to designed altitude displays great difference when the  launch time is different. The research results can provide theoretical reference for conceptual design and flight test.]]></description>
<pubDate>2015/11/9 16:21:58</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[YANG Xixiang, HOU Zhongxi and MA Zhenyu]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>YANG Xixiang, HOU Zhongxi and MA Zhenyu</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201505014]]></guid><cfi:id>327</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Hardware reinforcement designs and reliability analysis of unmanned aerial vehicle autopilots]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201505015]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The autopilot is the crucial device for a unmanned aerial vehicle to implement autonomous flights and missions. Most of the existing commercial autopilots have no hardware reinforcement, which will lead to a risk in carrying out some significant tasks. The analysis reveals that the control resolver is the module which performs the greatest impact on the security and the reliability in the composing of an autopilot. With the increasing fault-tolerance requirements, 4 reinforcements were respectively designed, namely, the single resolver reset reinforcement, the dual resolver hot backup reinforcement, and the dual host systems switched by hardware and software. Several simple devices such as repositors, counters, inverters, selectors, and additional codes inside the resolvers were used to build the reinforcements. The reliabilities varying with time of the reinforcements were emphatically studied and comparatively analyzed. With the simulation of the working mechanisms, the fault-tolerance performances, such as the abnormal output durations, of the reinforcements in fault treatments were analyzed. The calculations show that all the reinforcements can obviously enhance the reliability of the autopilot, of which the dual host systems increase the most. This research provides a meaningful direction to the tradeoff of the fault-tolerance performance, complexity, and cost in high reliability autopilot designs.]]></description>
<pubDate>2015/11/9 16:21:58</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[GUO Tianhao<sup>1</sup>, HOU Zhongxi<sup>1</sup>, JIANG Jingfei<sup>2</sup> and JIANG Hanqing<sup>1</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>GUO Tianhao<sup>1</sup>, HOU Zhongxi<sup>1</sup>, JIANG Jingfei<sup>2</sup> and JIANG Hanqing<sup>1</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201505015]]></guid><cfi:id>326</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Wind-induced responses of a rocket and its launching platform based on Davenport wind speed spectrum]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201505016]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[On the basis of Davenport wind speed spectrum and using M.Shinozuka method, samples of wind load were numerically simulated on the different girds of rocket core and booster under three basic wind velocities. Then a transient response analysis was made to the rocket and its launching platform by invoking the MSC.Nastran, and the displacement response of the rocket and its launching platform under different basic wind velocities was obtained. The value of the displacement increases along with the increase of height away from the ground, and the ratio of the maximal displacement approximates to the ratio of the square of basic wind velocity on a grid. Finally, a designed load-relieving structure was placed on the umbilical cord tower. Results indicate that the maximal displacement on different grids decreases conspicuously and the anti-wind capability of the rocket and its launching platform are enhanced by a large margin with the help of the load-relieving structure. The designed structure can make a reference to the engineering practice.]]></description>
<pubDate>2015/11/9 16:21:58</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[JIANG Guoqing and LI Daokui]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>JIANG Guoqing and LI Daokui</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201505016]]></guid><cfi:id>325</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Precision conversion methodology with truncated normal distribution theory assumption oriented to maximum-error specification]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201505017]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[A precision conversion methodology with truncated normal distribution theory assumption oriented to maximum-error specification was brought forward, and it could be taken as a reference frame for the precision conversion between maximum-error specification and other precision measurement specifications, so that the precision class of according true value measurement systems could be determined in advance. The method assumes that the conformity probability of the observation sequence is subjected to logarithmic truncated normal distribution; based on the aimed confidence level for maximum-error specification and the given sample size of target sequence, the calculation formulation of upper truncated limit, lower truncated limit, mean and standard deviation of the truncated normal distribution were proved and derived, thus the precision conversion relationships between maximum-error specification and other precision measurement specifications, such as  1σ, were turned out; through referring to the corresponding theories on precision instrument fields, the determination methodology for precision class of true value measurement systems under maximum-error specification was given. The application on related example cases proved the feasibility of the proposed method.]]></description>
<pubDate>2015/11/9 16:21:58</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[HAN Xu<sup>1,2</sup> and SUN Ao<sup>1</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>HAN Xu<sup>1,2</sup> and SUN Ao<sup>1</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201505017]]></guid><cfi:id>324</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Experimental investigation of combustion of boron particle agglomeration in secondary chamber]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201505018]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Investigation of boron particle agglomeration ignition and combustion in secondary chambers is very important for increasing the capabilities of ducted rockets. By experimentally mimicking ducted rockets, boron particle agglomeration ignition and combustion in secondary chamber flow field was investigated. The ignition and combustion processes, flame constructions and size changes of boron particle agglomeration were analyzed with the image processing techniques of high speed flame and the measurement results of flow field parameters. The effects of gas temperature and oxygen content on ignition and combustion of boron particle agglomeration were acquired. The analysis result of residue indicates that the particle size changes little and the gas may get into the boron particle agglomeration and react with boron particles.]]></description>
<pubDate>2015/11/9 16:21:58</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LIU Daoping<sup>1</sup>, XIA Zhixun<sup>1</sup>, HU Jianxin<sup>2</sup>, HUANG Liya<sup>2</sup> and FANG Chuanbo<sup>1</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LIU Daoping<sup>1</sup>, XIA Zhixun<sup>1</sup>, HU Jianxin<sup>2</sup>, HUANG Liya<sup>2</sup> and FANG Chuanbo<sup>1</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201505018]]></guid><cfi:id>323</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Gabor binary encoding for multi-sensor image matching]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201505027]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Multi-sensor image matching is a challenging problem in image process field. As synthetic aperture radar images and optical images have significant differences, most existing methods cannot achieve satisfied matching result. To respond to this issue, a new multi-sensor image matching method based on Gabor binary encoding was presented: the big and small input images were first convoluted respectively by a group of Gabor filters; the compressed representation was executed on the convolution result by using pooling method; the binarization of pooling results was conducted and it was transformed into binary code to create Gabor binary encoding features; the similarities of corresponding window features between real-time images and reference images were calculated by using bit manipulation and the maximum value indicated the matching result. This method describes images by binary representation, so the computation complexity is much lower than that of the traditional method, while the common characters are better revealed. Experimental results show that the proposed method has much higher matching rate and require much lower computation time than those of the existing methods.]]></description>
<pubDate>2015/11/9 16:21:59</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[TU Guoyong<sup>1,2</sup>, LI Zhuang<sup>1,2</sup>, ZHOU Shaobin<sup>1</sup>, LI Weijian<sup>1</sup> and YU Youhe<sup>3</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>TU Guoyong<sup>1,2</sup>, LI Zhuang<sup>1,2</sup>, ZHOU Shaobin<sup>1</sup>, LI Weijian<sup>1</sup> and YU Youhe<sup>3</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201505027]]></guid><cfi:id>322</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Overview of pseudo-spectral method and its application intrajectory optimum design for flight vehicles]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201504001]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Trajectory optimum design for flight vehicles using pseudo-spectral methods has been a hot research direction in recent years, but studies about the overview of this field are very few. Based on the systematic research of domestic and overseas related literatures, the basic principles of several pseudo-spectral methods which have a wide range of applications in aerospace field were expounded; the thoughts and formulas for transforming continuous optimal control problems into nonlinear programming problems were concluded; the applications of pseudo-spectral method in the trajectory optimum design for flight vehicles were summarized; the development directions of pseudo-spectral method and its application in trajectory optimization design for flight vehicles were discussed.]]></description>
<pubDate>2015/9/1 0:00:00</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[YANG Xixiang, YANG Huixin and WANG Peng]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>YANG Xixiang, YANG Huixin and WANG Peng</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201504001]]></guid><cfi:id>321</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Simulation on flow field characteristics of natural convection inside near space airship]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201504002]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Aiming at the near space airship, the natural convection characteristics of the helium inside an airship were simulated numerically. On the basis of the computational fluid dynamics method and user-defined function, external temperature boundary condition was imported into the wall grids. Under conditions of different steady states, the motion characteristics and influence regulations of gas natural convection inside the airship were analyzed by researching the characteristic parameters of flow field, such as distribution of pressure, temperature, speed. Besides, the unstable change process of natural convection was also studied preliminarily. The simulation results show that natural convection of helium inside a near space airship has some active influence on heat exchange of inside helium, but the influence is very weak on stressed skin and structural safety.]]></description>
<pubDate>2015/9/1 15:03:06</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[ZHANG Juntao, HOU Zhongxi, LIU Zhaowei and MA Zhenyu]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>ZHANG Juntao, HOU Zhongxi, LIU Zhaowei and MA Zhenyu</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201504002]]></guid><cfi:id>320</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Control allocation approach for stratospheric airship attitude control]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201504003]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The stratospheric airships  generally act with the redundant control effectors, thus a control allocation approach based on generalized inverse was applied to the airship attitude control system and the weighted pseudo-inverse control allocation method was adopted on the basis of characteristics of airship control effectors. The simulation results of a stratospheric airship attitude control show that: the designed control allocation approach can realize the coordinated operation of redundant control effectors effectively and its control effect on attitude angle is good, which avoids the premature saturation of control surface when using single effector; the reasonable adjustment of control allocation weights can reduce energy consumption, enhance instantaneity and provide convenience in engineering.]]></description>
<pubDate>2015/9/1 15:03:06</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[WANG Peng, HOU Zhongxi and YANG Xixiang]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>WANG Peng, HOU Zhongxi and YANG Xixiang</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201504003]]></guid><cfi:id>319</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Moving mesh strategy for large deformation of near-space aircrafts]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201504004]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The high-aspect-ratio low-speed near-space aircrafts may  undergo very large deformation during flight, so a high demand of moving mesh is required for the analysis method based on computational fluid dynamics. To this end, a moving mesh strategy for large deformation of the boundary was presented. The strategy which is based on the mapping interpolation method reflects the displacement of boundary mesh to flow field mesh using a certain kind of weight and then updates the position of mesh nodes. Inverse distance’s nth-power was chosen as the weighting factor and the influence of different weight index n on the mesh deformation was studied, then the analysis of some two-dimensional and threedimensional moving mesh cases was carried out. The results suggest that this method is capable of handling the large deformation and ensuring the quality of deformed mesh.]]></description>
<pubDate>2015/9/1 15:03:06</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LIU Zhaowei, HOU Zhongxi and CHEN Lili]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LIU Zhaowei, HOU Zhongxi and CHEN Lili</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201504004]]></guid><cfi:id>318</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Structural performance analysis of large-scale flexible inflatable structures for stratospheric airships]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201504005]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Taking inflatable structures of stratospheric airships as the main study object, the minimum differential pressure and the stress of inflatable structures were computed according to its design theory and a finite element model of inflatable structure for stratospheric airship was established. On the basis of the model verification, nonlinear finite element method was applied to simulate inflatable structural performance so as to obtain the distribution and change laws of the deformations and stresses of inflatable structure with the variations of pressure load and gondola load. The effects of structural reinforcement devices on the stress and deformation of inflatable structure also were evaluated. The simulation results can serve as reference for the structural design of the stratospheric airship.]]></description>
<pubDate>2015/9/1 15:03:06</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[MA Zhenyu, HOU Zhongxi and YANG Xixiang]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>MA Zhenyu, HOU Zhongxi and YANG Xixiang</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201504005]]></guid><cfi:id>317</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Numerical simulation of ducted rotor′s aerodynamic characteristics]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201504006]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Taking a ducted fan rotor as the study object, the reasons why open rotor and ducted rotor produce different lift were researched through the  momentum theory. At the same time, the three-dimensional Navier-Stokes equations and SST k-ω turbulence model were used to simulate the complex flow around the open and ducted rotor, which was based on the sliding mesh method. It also analyzed their differences in lift coefficient, power coefficient and efficiency at different rotating speed. The duct restrains tip vortexes and reduces energy wastage markedly, which make the lift coefficient increase 23% and the radio of lift and power coefficient augment 40%. Efficiency is obviously improved and the required power coefficient is slightly increased to 0.05. The results coincide with the theoretical analysis.]]></description>
<pubDate>2015/9/1 15:03:06</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LI Xiaohua, GUO Zheng and CHEN Qingyang]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LI Xiaohua, GUO Zheng and CHEN Qingyang</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201504006]]></guid><cfi:id>316</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Analysis of configuration characteristics and aerodynamic performance on longitude-latitude network inflatable wings]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201504007]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The inflatable wing is a good innovational conception for the near space solar-powered aircraft. The problems of configuration characteristics and aerodynamic analysis of inflatable wings were taken as the aim of the current study. First, configuration characteristics were analyzed and designed. Then the model of 3d network inflatable wing was developed. With computational fluid dynamics method, aerodynamic performances of 2d inflatable wing profile and 3d network inflatable wing were studied. Numerical simulation result shows that the aerodynamic performances of 2d inflatable wing profile and 3d network inflatable wing have reduced slightly at the design Reynolds number. Meanwhile, with the structure of flow field and mechanism analysis, the reason for the total drag coefficients of inflatable wings increasing significantly lies in that, in those bumpy areas of the inflatable wing, vortexes which cause the friction drag has a reduction in some extent, but the pressure drag has a significant increase, so the total aerodynamic performance decreases.]]></description>
<pubDate>2015/9/1 15:03:06</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[ZHANG Juntao, HOU Zhongxi and GUO Zheng]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>ZHANG Juntao, HOU Zhongxi and GUO Zheng</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201504007]]></guid><cfi:id>315</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Dynamics modeling of dynamic soaring and energy gaining from the wind gradient]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201504008]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In order to simplify the description of the problems and to be convenient for mathematical manipulation, a series of hypotheses about the dynamic glide problem of unpowered aircraft were made. Under these hypotheses, a dynamics model of dynamic soaring, which is a 3-dimentional ordinary differential equations in the velocity space with a single input, was built. The largest growing area of mechanical energy in this velocity space, which is called energy-gained spindle, was obtained theoretically and the maximum rate of energy increasing was also deduced. The conclusion that the larger wind gradient, the smaller drag and the smaller area-mass ratio are more in favor of gaining energy for the engines aircraft gives a deeper understanding of the dynamic soaring energy and it can help the practice. ]]></description>
<pubDate>2015/9/1 15:03:06</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[SHAN Shangqiu, HOU Zhongxi, ZHU Bingjie and GAO Xianzhong]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>SHAN Shangqiu, HOU Zhongxi, ZHU Bingjie and GAO Xianzhong</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201504008]]></guid><cfi:id>314</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Conceptual design of stratospheric airship basedon particle swarm optimization algorithm]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201504009]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Minimizing the total weight of a stratospheric airship reflects the design object of lowest total cost to a certain extent. To meet the power requirement of payload is the springboard and goal for the conceptual design of the airship. The model of paving solar cells on curved surface and the model of energy-closed loop during day and night were introduced in the parametric modeling of the airship. The particle swarm optimization algorithm was used to optimize the parameters of the  outside size. The design object is to find a feasible airship which has minimum total mass and satisfies the constraints with three balances: the diurnal balance between the energy supply and the energy requirement, the balance between mass and buoyancy, and the balance between drag and thrust. The sensitivity of the optimization results with different requirement of payload power and payload specific power was analyzed. The analysis results show that: the total airship weight increases linearly with the payload power; the total airship weight decreases steeply with the payload  power density, but the change rate of the total weight also decreases and the total weight tends to be stable. The results of energy system simulation indicate the validity of the conceptual design method, as well as the critical characteristics of the design results.]]></description>
<pubDate>2015/9/1 15:03:06</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LIU Duoneng, YANG Xixiang, MA Zhenyu and HOU Zhongxi]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LIU Duoneng, YANG Xixiang, MA Zhenyu and HOU Zhongxi</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201504009]]></guid><cfi:id>313</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Flight mode analysis for stratospheric airships]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201504010]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The aerodynamic shape, overall design and operation principle of stratospheric airships are different from the conventional aircrafts such as airplane and missile, and the flight mechanism. The dynamics characteristics of the stratospheric airship are different from the conventional aircrafts. Therefore, the inherent mechanism and characteristics of the stratospheric airship need to be further investigated. The linearization equations of motion for stratospheric airship were derived by using the “small disturbance” theory, which could be divided into longitudinal motion and lateral-directional motion. The fight modes and mode parameters were defined, and an analytical method was proposed to analyze the flight dynamics. Flight modes of the stratospheric airship were investigated based on eigenvalue and eigenvector of the state equations. Results show that the longitudinal motion includes three modes: heave mode, surge mode and pendulum mode, whereas the lateral motion includes another three modes: yaw mode, sideslip mode and roll oscillation mode.]]></description>
<pubDate>2015/9/1 15:03:06</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[YANG Yueneng, ZHENG Wei, YAN Ye and SHAO Hanbin]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>YANG Yueneng, ZHENG Wei, YAN Ye and SHAO Hanbin</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201504010]]></guid><cfi:id>312</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Development status and tendency of active debris removal]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201504020]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[With the increase of domestic and foreign launching tasks, it is becoming a serious challenge that plenty of failure or invalid spacecrafts in the process of space resources recycling. The active debris removal can be regarded as an effective and fundamental means that can realize the reuse of space resources and safe disposal. The concept of active debris removal is clarified and its development process also is analyzed. Some key techniques, such as relative navigation, coordinated control, capture method and device for non-cooperative target, are proposed. It will provide some fruitful reference for our country′s active debris removal in future.]]></description>
<pubDate>2015/9/1 0:00:00</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[CAO Xibin<sup>1</sup>, LI Feng<sup>1</sup>, ZHANG Jinxiu<sup>1,2</sup> and Richard Muriel<sup>2</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>CAO Xibin<sup>1</sup>, LI Feng<sup>1</sup>, ZHANG Jinxiu<sup>1,2</sup> and Richard Muriel<sup>2</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201504020]]></guid><cfi:id>311</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Experiment on the propagation mode of continuous rotating detonation wave]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201504021]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Experiments on continuous rotating detonation wave of H<sub>2</sub>/air were performed with constant air mass flow rate and varied H<sub>2</sub>/air equivalence ratio(ER). Three different propagation modes of the continuous rotating detonation wave were found as the decreasing of ER, namely, one direction mode at high ER from 0.90 to 1.86, two-wave collision propagation mode at low ER of about 0.75, hybrid mode of one direction mode and two-wave collision propagation mode at middle ER. The propagation characteristics of the high-frequency pressures were analyzed and the mode transition mechanism of continuous rotating detonation wave was preliminarily studied. With a higher ER, the strength of the detonation wave is increased and the loss and velocity deficit during the propagation  are relatively small, and the continuous rotating detonation wave can be sustained in the one direction mode; while with a lower ER, the strength of the continuous rotating detonation wave is reduced and the influence of the loss and velocity deficit during the propagation  is relatively enlarged, only in the two-wave collision propagation mode can the continuous rotating detonation wave be sustained. This can be attributed to the collision of the two counter-propagating shock waves in the two-wave collision propagation mode, which will promote the heat release,  will enable the continuous rotating detonation wave to propagate steadily at a low ER, and will make the two-wave collision propagation mode possibly be the ultimate propagation mode of continuous rotating detonation wave. ]]></description>
<pubDate>2015/9/1 15:03:07</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[WANG Chao, LIU Weidong, LIU Shijie, LIN Zhiyong and JIANG Luxin]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>WANG Chao, LIU Weidong, LIU Shijie, LIN Zhiyong and JIANG Luxin</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201504021]]></guid><cfi:id>310</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Midcourse guidance of interception using state transition matrix]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201504023]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[On the basis of relative motion theory, a midcourse guidance method of exoatmospheric interception was developed. The mechanism of this method is that treating the initial and modified trajectories as chief and deputy space objects respectively, modeling the dynamics of the deputy relative to the chief by the relative motion theory and solving the initial corrections through the final relative states. The universal relative motion model was provided and then the state transition matrix of relative motion under the influence of J<sub>2</sub> disturbance was derived by employing the geometry and the variation method. Lastly the midcourse guidance method using state transition matrix was proposed on this basis. Simulation example shows that the proposed method serves as an efficient support for midcourse guidance of interceptors in practice.]]></description>
<pubDate>2015/9/1 15:03:07</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[CHAI Hua<sup>1</sup>, ZHONG Ming<sup>2</sup> and LIANG Yangang<sup>1</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>CHAI Hua<sup>1</sup>, ZHONG Ming<sup>2</sup> and LIANG Yangang<sup>1</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201504023]]></guid><cfi:id>309</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Manned lunar exploration of human-machine combination based on staging method]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201504024]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The construction mode of manned lunar spacecraft was designed by using the classic staging combination design method of lunar spacecraft. A preliminary estimation of the rocket carrying capacity was made according to the analysis of the different staging methods, and the exploration schemes of human-machine synergy are obtained as well. The staging method can provide a new solution to orbit transfer vehicle and landing craft design. The mass estimation of lunar craft based on the analysis of different staging options was given, and the corresponding rocket carrying capacity of different flight modes was compared. The study can provide reference to the scheme of our country’s first manned lunar mission.]]></description>
<pubDate>2015/9/1 15:03:08</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[ZHANG Yakun and LI Haiyang]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>ZHANG Yakun and LI Haiyang</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201504024]]></guid><cfi:id>308</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Nonlinear numerical simulation of cavity noise]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201504025]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In order to evaluate the M219 cavity noise at 0.6, 0.85 and 1.35 Mach number, nonlinear acoustic solver is combined with Reynolds-averaged Navier-Stokes equations. The flow field of a cavity is calculated by means of Reynolds-averaged Navier-Stokes equations, which contains basic characteristics of average flow field and turbulence statistical average solution of statistics description of turbulence fluctuation. Noise source is refactored by the nonlinear acoustic solver. Spread of pressure fluctuation is simulated precisely. A comparison shows that the simulation results of nonlinear acoustic solver agree well with the experiment results. Compared with detached eddy simulation，nonlinear acoustic solver can greatly reduce the amount of mesh. In addition, the method can provide some reference for internal weapons bay design. ]]></description>
<pubDate>2015/9/1 15:03:08</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[WANG Yiding<sup>1</sup>, CHEN Binqi<sup>1</sup>, GUO Liang<sup>2</sup>, ZHONG Fanjun<sup>2</sup> and TONG Mingbo<sup>1</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>WANG Yiding<sup>1</sup>, CHEN Binqi<sup>1</sup>, GUO Liang<sup>2</sup>, ZHONG Fanjun<sup>2</sup> and TONG Mingbo<sup>1</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201504025]]></guid><cfi:id>307</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Multicriteria forecast models of antimissile single/multiple impact points]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201504029]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The whole antimissile process can be viewed as an iteratively process based on impact points forecasting which showes that impact points was mainly focused on by present research in the following way. The time-space requirements for impact points forecasting were analyzed, and 3 forecasting criterions were proposed. The antimissile single impact points forecasting model at 3 criterions was established, and the unknown variables of the model were changed into values which radar can measure. For shoot-look-shoot scenario and shoot-shoot scenario, antimissile multiple impact points forecasting and optimization model was gave at 3 criterions, and the calculating method of latest launch time was discussed. The impact of different look occasion was analyzed and modeled during impact points forecasting process. Partial theories and methods was exploratory research, related conclusions made may be benefits for antimissile sustained shooting decision making.]]></description>
<pubDate>2015/9/1 15:03:08</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LI Longyue, LIU Fuxian, YANG Guozhe, WANG Dongxu and WANG Ju]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LI Longyue, LIU Fuxian, YANG Guozhe, WANG Dongxu and WANG Ju</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201504029]]></guid><cfi:id>306</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Analysis and design of phasing strategy for near-earth short rendezvous mission]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201503011]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Based on the two-day profile of Chinese rendezvous and docking mission, a 5-revolution short-rendezvous phasing strategy was proposed by cutting down the flight duration for orbit determination, computation of maneuver parameters and command uploading, and non-visible course of flight. This phasing strategy was solved by using the algorithm of four-impulse modified special-point maneuver. The required precision of orbit determination to meet the control precision at the end of phasing was obtained. Then, the optimal phase range and total velocity increment were analyzed. Further results show that the optimal phase range is affected by the target spacecraft’s orbit injection accuracy, the chaser’s orbit insert precision and apogee height, the target orbital altitude and the final desired target point of rendezvous phasing. Finally, in order to obtain the starting phase angle, both the target spacecraft’s phasing strategy and the chaser’s launch chances are analyzed for the short rendezvous mission.]]></description>
<pubDate>2015/6/30 18:53:56</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[YANG Zhen, LUO Yazhong and ZHANG Jin]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>YANG Zhen, LUO Yazhong and ZHANG Jin</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201503011]]></guid><cfi:id>305</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[The deployment dynamic characteristics analysis of space web system]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201503012]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Space web system is a new type of lightweight flexible space structure, which indicates great potential application value.  Firstly, according to different mechanical environment in space and on the ground, the dynamic model of space web was established. Then, the reliability of the simulation model was validated by the ground test. Finally, based on performance parameters, for instance, deployment area, flight distance, etc, the dynamic characteristics were simulated and analyzed, such as the web shape, stress distribution and energy change, and the influence of the orbit height, capture direction and casting parameters on the deployment process were also analyzed.]]></description>
<pubDate>2015/6/30 18:53:56</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LIU Haitao, ZHANG Qingbin, YANG Leping and ZHU Yanwei]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LIU Haitao, ZHANG Qingbin, YANG Leping and ZHU Yanwei</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201503012]]></guid><cfi:id>304</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Parallel computation of compressible turbulence using multi-GPU clusters]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201503013]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Based on CUDA Fortran for compressible turbulence simulations, a finite volume computational fluid dynamics solver on the GPU(Graphical Processing Unit） was developed. The solver was implemented with an AUSMPW+ scheme for the spatial dispersion, the k-ω SST model for turbulence model, and MPI communication for parallel computing. Some optimization strategies for fluxes computation and multi-GPU parallel algorithms for overlap of PCIe data transfer and MPI communication with GPU computation have been discussed for the latest generation GPU architecture. Several test cases, such as a supersonic inlet and a space shuttle were chosen to demonstrate the acceleration performance of GPU on large-scale grid size. Results show that when using a NVIDIA GTX Titan Black GPU, the computational expense can be reduced by 107～125 times than using a single core of an Intel Xeon E5-2670 CPU. Fast computing for a complex configuration with 0.134 billion grid sizes has been achieved by using 4 GPUs and the parallel efficiency is 91.6%.]]></description>
<pubDate>2015/6/30 18:53:56</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[CAO Wenbin, LI Hua, XIE Wenjia and ZHANG Ran]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>CAO Wenbin, LI Hua, XIE Wenjia and ZHANG Ran</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201503013]]></guid><cfi:id>303</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Performance analysis of propulsion system of miniature electric-powered  vertical takeoff and landing air vehicles]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201503014]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The hover duration performances of miniature VTOL(Vertical Takeoff and Landing) air vehicles depend on the performance of propulsion system. Based on the mass models of battery, motor and ESC(Electronic Speed Controller), and the relationship between provided force and required power of propeller, the duration calculation model of vertical takeoff and landing air vehicles was established by using the battery constant-current discharge model. The influence of propulsion parameters and payload on vehicle duration is analyzed, which would be used for preliminary design of VTOL air vehicles and components selection of propulsion system.]]></description>
<pubDate>2015/6/30 18:53:56</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[WANG Bo, HOU Zhongxi and WANG Wenkai]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>WANG Bo, HOU Zhongxi and WANG Wenkai</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201503014]]></guid><cfi:id>302</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Analysis on the altitude stability of missile with coning motion-based control]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201503016]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In view of the effect of coning motion on missile stability, a nonlinear mathematical model of missile coning motion control was established. By introducing the concept of complex attack angle, the nonlinear model that was difficult to be resolved by analytical means could be transformed to a general resolvable model. According to the linear model of the missile complex attack angle motion equations, the range of stability control of the guidance and control system parameters were deduced, the influence of damping loop and control loop of control system on the stability of missile coning motion was analyzed, and the method to judge the stability of coning motion control was proposed. Simulation results validate the feasibility and correctness of this method, which provides a reference for the design of missile coning motion of guidance and control system.]]></description>
<pubDate>2015/6/30 18:53:56</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[DUAN Xiaoju<sup>1</sup>, SUN Ruisheng<sup>2</sup>, BAI Hongyang<sup>2</sup> and XUE Xiaozhong<sup>2</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>DUAN Xiaoju<sup>1</sup>, SUN Ruisheng<sup>2</sup>, BAI Hongyang<sup>2</sup> and XUE Xiaozhong<sup>2</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201503016]]></guid><cfi:id>301</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[On-line aerial photogrammetry method using embedded technology]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201503017]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In order to meet the demand of real-time spatial data processing and improve the online processing capability of photogrammetric system, a kind of online photogrammetry method is proposed. According to the proposed method, system based on embedded architecture is then designed. Online photogrammetric data processing is realized by using FPGA(Field Programmable Gate Array), ARM+DSP(Advanced RISC Machine coupled with Digit Signal Processor) and other embedded computing technologies to build specialized hardware operating environment as well as transplanting and optimizing the existing photogrammetric algorithm to the embedded system. Aerial photogrammetric experiment shows that the method can achieve high-speed and stable online processing of photogrammetric data. And the experiment also verifies the feasibility of the proposed online photogrammetric system based on embedded architecture, which can improve the processing the efficiency of photogrammetry to a higher level and broaden the application field of photogrammetry.]]></description>
<pubDate>2015/6/30 18:53:56</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[GUI Li, ZHENG Shunyi, WANG Xiaonan and MA Dian]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>GUI Li, ZHENG Shunyi, WANG Xiaonan and MA Dian</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201503017]]></guid><cfi:id>300</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Multi-camera trajectory triangulation for point target motion measurement in different conditions of time information]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201503018]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Multi-camera trajectory triangulation is proposed to determine a point target trajectory in different conditions of time information. The target trajectory is parameterized by time polynomial. The motion parameters can be determined by triangulating the series of sight rays of multi-camera and the target trajectory where the object space collinearity error is minimized. In contrast with the traditional triangulation, this method can not only get higher precision, but also adapt to the conditions of asynchrony, no time registration or even no time information among multi-camera. In contrast with the monocular system, there is no request of camera motion. Synthesized and real data experiments show the validity and high precision of the proposed method.]]></description>
<pubDate>2015/6/30 18:53:57</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LI Xin<sup>1,2</sup>, LIU Jiannan<sup>1,2</sup>, YANG Xia<sup>1,2</sup> and YU Qifeng<sup>1,2</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LI Xin<sup>1,2</sup>, LIU Jiannan<sup>1,2</sup>, YANG Xia<sup>1,2</sup> and YU Qifeng<sup>1,2</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201503018]]></guid><cfi:id>299</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Enriched finite element method for dissimilar material  interface crack]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201503019]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The enriched finite element method is used to solve the stress intensity factors for two bonded dissimilar materials containing a crack along the bond. By appending the displacement expressions for an interface crack to the common element, the enriched and transition element displacement model are obtained; the enriched finite element equation is derived. Two enrichment schemes are introduced to establish the finite element models for square plate center interface crack and rectangular plate unilateral oblique interface crack. The stress intensity factors are calculated directly from the finite element equation. The results, which are obtained by compared with analytical results, demonstrate that the enriched finite element method is a convenient and high precision calculation method for interface crack problems.]]></description>
<pubDate>2015/6/30 18:53:57</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[YANG Junhui<sup>1,2</sup>, LEI Yongjun<sup>1</sup> and MENG Shangyang<sup>2</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>YANG Junhui<sup>1,2</sup>, LEI Yongjun<sup>1</sup> and MENG Shangyang<sup>2</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201503019]]></guid><cfi:id>298</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Continuous self-calibration and self-alignment method for floated inertial platform]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201503024]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[A continuous self-calibration and self-alignment method based on attitude angle was proposed for the calibration and initial alignment of floated inertial platform (FLIP) system. According to the working principles of floated platform, the inertial sensor error models were built and the attitude dynamic model for the FLIP was established; in order to make the platform to be rotated in the gravity plane, the torquing policy was designed; using the theory of piece wise constant system (PWCS) and output sensitivity, the observability of system was analyzed. Finally, the proposed method was verified by simulations. The simulation results show that the proposed method can synchronously calibrate and align 42 error coefficients of the FLIP with high accuracy and significantly improve the measurement precision of the system. ]]></description>
<pubDate>2015/6/30 18:53:57</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[DING Zhijian<sup>1</sup>, CAI Hong<sup>1</sup>, YANG Huabo<sup>1</sup> and LIAN Dinglei<sup>2</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>DING Zhijian<sup>1</sup>, CAI Hong<sup>1</sup>, YANG Huabo<sup>1</sup> and LIAN Dinglei<sup>2</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201503024]]></guid><cfi:id>297</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Evaluation method for hypersonic vehicle 
trajectory optimization]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201502022]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Comprehensive evaluation for hypersonic vehicle trajectory optimization algorithm has good reference value on selecting optimal trajectory optimization algorithm. According to the features of hypersonic vehicle, trajectory was decomposed into ascent, cruise and descent stages; the performance evaluation indices of each stage and the typical methods of weighting for performance evaluation index were given respectively. Combining with the analysis theory of grey correlation degree, a comprehensive evaluation method of trajectory optimization algorithm was proposed. The calculation results show that the method can quantitatively evaluate trajectories produced by trajectory optimization methods and sort the alternative optimization methods by merits.]]></description>
<pubDate>2015/5/16 9:33:25</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[HU Huaizhong, GUO Rushuang, GONG Houjuan and WEI Shilei]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>HU Huaizhong, GUO Rushuang, GONG Houjuan and WEI Shilei</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201502022]]></guid><cfi:id>296</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Deployment optimization method for ground-based radar 
to detect near space hypersonic target]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201502023]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In order to improve detection ability of groundbased radar to near space hypersonic target and explore a practical and efficient deployment optimization method, the difficulties and mathematical models of the ground-based radar to detect near space hypersonic target were analyzed and the deployment principle and quantitative indicators of it were put forward. Deployment optimization model of ground-based radar was established and the ant colony algorithm controlled by introductory pheromone was designed. The simulation results show that this method can achieve a variety of programs of ground-based radar deployment optimization, improve the efficiency and operability of the ground-based radar deployment optimization, and provide a new way of thinking for ground-based radar to detect near space hypersonic target.]]></description>
<pubDate>2015/5/16 9:33:25</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[XIAO Song, TAN Xiansi, WANG Hong and WANG Yi]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>XIAO Song, TAN Xiansi, WANG Hong and WANG Yi</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201502023]]></guid><cfi:id>295</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Analyzing perturbation characteristic and orbital maintenance 
strategy for super low altitude satellite]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201502024]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Aiming at the orbital maintenance problem of super low altitude satellite for the long duration of the flight, the variation characteristics of the average eccentricity vector were analyzed and an orbital maintenance method was presented. Firstly, the change of average eccentricity vector characteristic of super low altitude satellite under the J<sub>2</sub>,J<sub>3</sub> zonal terms and the atmospheric drag was analyzed. Then an orbital maintenance strategy based on energy conservation principle was proposed. Finally, the effectiveness of orbital maintenance strategy was validated by simulation examples. Simulation results show that the changes of average eccentricity is stable under the perturbation of the earth non-spherical gravity, the atmospheric drag and the impulsive maneuver, and the proposed orbital maintenance method can effectively achieve super low altitude maintenance and make the average eccentricity vector converge to equilibrium point. Besides, the fuel consumption for orbital maintenance is reasonable and the long duration flight in super low orbit can be achieved.]]></description>
<pubDate>2015/5/16 9:33:25</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[WEN Shenglin, YAN Ye and YI Teng]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>WEN Shenglin, YAN Ye and YI Teng</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201502024]]></guid><cfi:id>294</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[A new numerical simulation algorithm for the reconstruction of X-ray pulsar signal]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201502026]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[For navigation using X-ray pulsars, both technique investigation and simulation were based on the X-ray pulsar signal. But practically, the observation data was unable to confirm the exact value or the analysis of validation of navigation algorithm. Therefore, it was necessary for simulation algorithms to reconstruct X-ray pulsars. Based on the fact that the arrival of photons possess non-homogeneous poisson random process, the model of the signal of X-ray pulsars was built, and the epoch folding algorithm for pulse profile construction was presented. Two existed simulation algorithms were presented. A new numerical simulation algorithm based on the reconstruction of photon TOAs (time of arrivals) was derivated from distributive function and its inverse function. To avoid approximating in the two algorithms, the derivated algorithm employed the pulse profile fitted by piecewise linear function. The signal of pulsar PSR B0531 +21 was simulated, and chi-square goodness-of-fit-test was utilized to demonstrate that the simulated TOAs complied with the poisson distribution. Comparison was implemented among the new algorithm and the existed two algorithms. Simulation result indicates that the new algorithm is superior to the existed two algorithms in photon counts and pulse profile error. Observed pulse profiles approaches to the standard template profile as observation time increases, which demonstrate that the simulation algorithm is feasible, and the X-ray pulsar signal can be reconstructed effectively. ]]></description>
<pubDate>2015/5/16 0:00:00</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[GUI Xianzhou, HUANG Senlin and SUN Chen]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>GUI Xianzhou, HUANG Senlin and SUN Chen</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201502026]]></guid><cfi:id>293</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Application of BP neural network model in prediction of polar motion]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201502028]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[A predictive model was set up to improve the prediction precision of polar motion of earth orientation parameters. The periodic characteristics of interpolated basic series was studied by Fourier analysis, the feasibility of basic series resampling was verified, then the trend terms were derived from the interpolation basic series, and the multiple input-single output BP(Back Propagation)neural network model was used to predict the residual series for different time spans. Finally the predicted polar motion was achieved by combining the trend terms with residual series. Prediction results indicate that the appropriate selection of interpolation basic series can realize high precision prediction of polar motion. Moreover, the BP neural network can be applied to the prediction of polar motion of earth orientation parameters effectively.]]></description>
<pubDate>2015/5/16 9:33:25</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[ZHANG Zhi<sup>1</sup>, LIAO Ying<sup>1</sup> and YU Yue<sup>2</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>ZHANG Zhi<sup>1</sup>, LIAO Ying<sup>1</sup> and YU Yue<sup>2</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201502028]]></guid><cfi:id>292</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Star spot centroiding method with 
inertial measurement information]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201502029]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[As for the low centroid precision of blurry star spots acquired by the star sensor in vibration environment, the star spot centroiding model with inertial measurement information was proposed and the centroiding algorithm was formed. The weighted center of the star spot was regarded as the centroid at the initial time of the exposure by the algorithm, then the centroid track could be computed with the vibration information by the strap-down inertial sensor, and the star imaging area and its weighted center could be estimated with the star spot power distribution model. Finally, the exact centroid value at the finish time of the exposure was got by using iterative operation to make the two weighted centers coincide with each other. The centroiding precision of the algorithm and the effect of relevant factors on it are analyzed by using simulation data, and numerical results indicate that the method can reach about 0.01-pixel centroid precision even in the vibration environment with a good applicability performance.]]></description>
<pubDate>2015/5/16 9:33:25</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LYU Hanfeng, ZHANG Liang, WANG Dingjie and WU Jie]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LYU Hanfeng, ZHANG Liang, WANG Dingjie and WU Jie</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201502029]]></guid><cfi:id>291</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Design and implement of a NAND Flash controller with pipelining program 
and non-missing invalid block handle method]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201501009]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Aiming at requirement of high speed and complete of data in space storage system, the design of a high performance NAND Flash controller is present. It concludes a pipelining-programming inside of NAND Flash chip and a non-missing invalid block method. The storage implementation is present. The calculation of storage time in different situation is discussed. The simulation modules are present and the impact of pipelining programming is simulated and discussed using Monte Carlo method. Practical application proves the pipelining programming and non missing invalid block method. The operation frequency of storage system achieves to 100MB/s, ensuring accuracy, completeness and continuity of data.]]></description>
<pubDate>2015/3/19 11:35:43</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[YAN Mengting<sup>1，2</sup> and AN Junshe<sup>2</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>YAN Mengting<sup>1，2</sup> and AN Junshe<sup>2</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201501009]]></guid><cfi:id>290</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Zero propellant maneuver path existence analysis for space station]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201501010]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Zero-propellant maneuver is an advanced concept of attitude control, which has been applied to the International Space Station. The dynamic models of space station using control momentum gyros are constructed, and the momentum equilibrium relation between space station and control momentum gyros is established. Then, considering different large angle attitude mission, the relation between inertia of space station and characteristic parameters of control momentum gyros is analyzed, and conditions of zero-propellant maneuver path existence are obtained. Effectiveness of the existence conditions is verified by the path planning examples. The proposed existence conditions can provide a convenient and effective method to determinate whether the zero-propellant maneuver path exists, which can provide significant theoretical argument for zero-propellant maneuver technology to apply to Chinese Space Station in future.]]></description>
<pubDate>2015/3/19 11:35:43</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[ZHAO Qian<sup>1</sup>,HUANG Haibing<sup>1</sup> and LI Yi<sup>2</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>ZHAO Qian<sup>1</sup>,HUANG Haibing<sup>1</sup> and LI Yi<sup>2</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201501010]]></guid><cfi:id>289</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Design and on-orbit application of TT-1 satellite-based 
automatic identification system]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201501011]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The technology advantages and application prospects of satellite-based automatic identification system (AIS) were introduced, and then the system of the satellite based AIS of  TT-1  was designed to overcome the problems of multi-cell signal collision, Doppler shift and large space link attenuation, originating from the development of ground-based AIS to satellite-based AIS. This design included the composition of system, the qualification and function of AIS receiver, the design of antenna and microwave switch and the link level estimation of satellite-ground AIS. For the preparation of space applications, it mainly discussed the performance and environment test for the AIS receiver.The on-orbit application situation of  TT-1 satellite based AIS was introduced and the results show that the innovated AIS receiver can partly ease these technical problems and achieve a wide range of maritime surveillance requirements.]]></description>
<pubDate>2015/3/19 11:35:43</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[CHEN Lihu,CHEN Xiaoqian,ZHAO Yong and CHENG Yun]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>CHEN Lihu,CHEN Xiaoqian,ZHAO Yong and CHENG Yun</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201501011]]></guid><cfi:id>288</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Numerical simulation of detonation onset by hot jets]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201501012]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[An improved uncoupled solver of non equilibrium flow was adopted to resolve the Euler reacting equations and a chemical H<sub>2</sub>/air mixture reaction model with 9 species and 21 equations was employed to conduct the two-dimensional numerical simulation in detonation onset process of vertical hot jets. The convection term was dispersed with fifth-order WENO format and the time integration was iterated with second-order Runge-Kutta scheme. The flow fields in the detonation tube were analyzed in detail when hot jets were injected with different parameters (i.e.incident velocities, incident positions, incident widths and incident angles). And the general rule of the impact of hot jets parameters to the detonation initiation was summarized. Moreover, interaction between shocks and flame during the formation and propagation of “hot spots” was explained, especially the promotion of reflected shocks on the formation of “hot spots”. The investigation reveals that detonation always occurs from the “hot spots” in narrow unburned region which is confined by adjacent flame front and solid wall. Triple point structures emerge during the over-driven transition of “hot spots” to detonation. In order to achieve rapid detonation onset, the hot jets should be injected towards the side wall in high velocity and with a certain angle.]]></description>
<pubDate>2015/3/19 11:35:43</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LIN Wei,ZHOU Jin,LIN Zhiyong and LIU Shijie]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LIN Wei,ZHOU Jin,LIN Zhiyong and LIU Shijie</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201501012]]></guid><cfi:id>287</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Energy transformation in dynamic soaring of unmanned aerial vehicles]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201501013]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Dynamic soaring is a special flying technique designed to allow air vehicles to extract energy from atmosphere. Based on the established dynamic model of the aircraft, the energy transformation of unmanned aerial vehicles (UAVs) in a gliding cycle of the known gradient wind field was analyzed. The method of subsection analysis was introduced and a dynamic soaring cycle was divided into four phases: climbing with headwind, turning in high altitude, gliding with tailwind, turning in low altitude. Turning in high altitude was the most critical phase in the dynamic soaring cycle. By using the calculation method which combines the three-dimensional space path with the two-dimensional plane projection, the motion equation and energy transformation equation of UAV in the phase of turning in high altitude were achieved. Based on the equations, the parameters which influenced the energy extract of UAVs from gradient wind field and which resulted in the energy loss because of the wind drag were analyzed. The conclusion provides theoretically guide for the UAV’s maximum extracted energy from gradient wind field and the decreasing of its energy loss. Besides, the dynamic soaring simulation was designed and results show that the phase of climbing with headwind and the early stage of turning in high altitude are the mainly periods to absorb energy from wind field. This conclusion is meaningful to direct the dynamic soaring without thrust.]]></description>
<pubDate>2015/3/19 11:35:43</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[ZHU Bingjie and HOU Zhongxi]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>ZHU Bingjie and HOU Zhongxi</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201501013]]></guid><cfi:id>286</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Fluid-structure interaction characteristics analysis 
of vortex ring parachute]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201501014]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Based on arbitrary Lagrange-Euler fluid-structure interaction method, the inflation process of a typical kind of vortex ring parachute in an infinite mass situation was simulated. The inflation process and the time-history changing curves of spinning rate and opening load were obtained, and the fluid-structure interaction characteristics at the steady stage, such as the change law of flow field around the canopy and the structural strength of the canopy fabrics, were analyzed. Results show that the stable spinning rate is about 3.1r/s and the canopy inflated shape is plump with the flow velocity of 12m/s, which are in good agreement with the tower test data. In steady state, there are a plenty of vortex cores above the parachute, and the ligature of the cores is similar to a spiral line. The drag coefficient of vortex ring parachute is greater than that of other typical parachutes with axial symmetry structure. The stress of the connected region of the canopy and the suspension lines and the canopy fringing field are obviously greater than the average stress of the canopy.]]></description>
<pubDate>2015/3/19 11:35:43</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[MA Xiaodong,GUO Rui,LIU Rongzhong and LYU Shengtao]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>MA Xiaodong,GUO Rui,LIU Rongzhong and LYU Shengtao</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201501014]]></guid><cfi:id>285</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Evaluation method of pseudo range precision for ground-based 
pseudolite navigation system]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201501015]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The pseudo range and the precision of pseudo range variability from ground-based pseudolite navigation system are very important to the navigation performance of evaluation system and the fusion of pseudo range information with the navigation information from other system. At present, the evaluation methods of pseudo range precision are basically aimed for satellite navigation system and they don't take full account of the characteristics of ground-based pseudolite navigation system. By constructing the precision observations of pseudo range and its variability and utilizing some bad positioning configurations produced by ground-based pseudolite navigation system, a precision evaluation method for pseudo range and its variability which can get accurate precision estimator even the exterior ballistic measuring system has low position-velocity precision and owns arm length was proposed. The simulation results indicate that the method can evaluate the precision of pseudo range and its variability effectively and has a strong applicability. ]]></description>
<pubDate>2015/3/19 11:35:44</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LYU Hanfeng,ZHANG Liang and WU Jie]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LYU Hanfeng,ZHANG Liang and WU Jie</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201501015]]></guid><cfi:id>284</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Ignition algorithm for attitude control solid-propellant 
nozzles in kinetic interceptor]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201501016]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Using solid-propellant nozzles is one of the best schemes for kinetic interceptor to realize the fast response and high precision of attitude control. A mixed searching algorithm for ignition combination was presented for a novel attitude control solid-propellant nozzle in kinetic interceptor. Firstly, the configuration of solid-propellant nozzles was described and spin requirements of the kinetic interceptor were analyzed. Then the mixed searching algorithm was designed by a combination of sorting method and interval searching method. Sorting method is selected when the number of available nozzles is small and interval searching method is chosen on the contrary. Results of instruction torque approximation simulation and attitude control numerical simulation suggest that the algorithm can track the instruction torque effectively and achieve attitude tracking quickly and with a high precision.]]></description>
<pubDate>2015/3/19 11:35:44</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LI Guanghua,ZHANG Hongbo and TANG Guojian]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LI Guanghua,ZHANG Hongbo and TANG Guojian</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201501016]]></guid><cfi:id>283</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Energy balance simulation of board nano-satellite power system]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201501017]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Energy balance is the basic requirement in designing and evaluating the power system of nano-satellite, and it is often examined by numerical simulation on ground. The architecture and feature of the board nano-satellite power system was introduced first. Then the mathematical models of solar array, Li-ion battery and satellite load were developed respectively. At last, the energy balance was simulated by combining the satellite attitude dynamics. The simulation result can reflect the power change, battery capacity and state of energy balance in real time. The data of on-orbit experiment is consistent with the simulation results, which show that the models are correct and the simulation method is feasible.]]></description>
<pubDate>2015/3/19 11:35:44</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[SHENG Tao,BAI Yuzhu,ZHAO Yong,CHEN Xiaoqian and CHEN Lihu]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>SHENG Tao,BAI Yuzhu,ZHAO Yong,CHEN Xiaoqian and CHEN Lihu</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201501017]]></guid><cfi:id>282</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Air inlet property analysis of the air-breathing solar thermal propulsion]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201606010]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Air-breathing scramjet propulsion is the basis of air-breathing solar thermal propulsion technology. How to design an ideal air-inlet is crucial for the propulsion system. By taking advantage of the  common method, the DSMC(direct simulation Monte Carlo)  on rare-field gas dynamics research, was made to simulate two kinds of air-inlets, which obtained a lot of air parameters such as temperature, density, coefficient of flow and velocity. Then it selected a better air-inlet shape from comparison and treated the shape as a basic air-inlet shape in airbreathing solar thermal propulsion system. It lays a foundation for the design, computation, analysis and optimization on the whole system.]]></description>
<pubDate>2016/12/31 18:39:26</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[HUANG Minchao and DU Yunliang]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>HUANG Minchao and DU Yunliang</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201606010]]></guid><cfi:id>281</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[ARMA-based stochastic modeling method for improving the performance of low-cost MIMU/GNSS integration]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201606011]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[High noise and complicated errors caused by low-cost MIMU (micro-electro-mechanical system-based inertial measurement unit, MEMS-based IMU) have caused its stochastic modeling challenge, which may undermine the performance of inertial-based integrated navigation. In order to achieve accurate MEMS-based navigation, a stochastic modeling method called auto-regressive moving-average model for low-cost MEMS-based inertial sensors was proposed on the basis of time series analysis theory. This model was then expanded into the state variables of the conventional Kalman filter to establish the system dynamic equation and observation equation and to estimate the zero-bias online. Field test results indicate that the proposed algorithm can not only realize a highly accurate autonomous navigation for lowcost MIMU, but also provide reliability to the MIMU/GNSS integrated system. ]]></description>
<pubDate>2016/12/31 18:39:26</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[WANG Dingjie, LYU Hanfeng and WU Jie]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>WANG Dingjie, LYU Hanfeng and WU Jie</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201606011]]></guid><cfi:id>280</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Vortex-induced vibration with shear flow]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201606012]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The initial and boundary condition, the hydrodynamic force on the cylinder surface and the cylinder response equations with shear flow were derived based on the stream function-vorticity equations in the exponential-polar coordinates attached on the moving cylinder. The whole evolutions of cylinder starting from rest and then undergoing development and vibration steady were calculated and discussed. The development process of separation vortexes, the deformation and shift of drag-lift phase diagram and the variation of cylinder vibration and equilibrium position were described. Moreover, the steady condition of vortex-induced vibration with the shear rate K was investigated. The results show that the symmetrical flow field will be broken due to the background vorticity  generated by the shear flow which also causes the increase of upper vortex strength and the decrease of lower vortex strength. The vortex street inclines toward the lower side and the inclination of vortex streets increase with the increasing shear rate K. So does the shift of pressure curves which leads to the increase of absolute value of lift, the amplitude and the shift of cylinder.]]></description>
<pubDate>2016/12/31 18:39:26</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[ZHANG Hui, LIU Mengke, FAN Baochun and CHEN Zhihua]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>ZHANG Hui, LIU Mengke, FAN Baochun and CHEN Zhihua</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201606012]]></guid><cfi:id>279</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Low-thrust trajectory design of rendezvous based on polynomial function]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201606013]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Shape-based approximation is an effective method for the low-thrust trajectory design. However, the vast majority of methods assume that the motion trajectory is a specific shape, and there is no constraint on the thrust acceleration. In this representation, according to the issue of low-thrust spacecraft rendezvous, a new method for transfering trajectory design was proposed. Based on the polar coordinates, the trajectory design was successfully turned into solving polynomial coefficients problem through three degrees of freedom motion model  built by introduced polynomial function. Meanwhile, the dynamic characteristics of the trajectory as well as the constraint equations were deduced. Subsequently, the optimal polynomial coefficients were solved by the approach of sequential quadratic programming. This method can not only  solve problems with a greater number of free parameters, but also  meet the thrust acceleration constraints. The simulation has confirmed that this method is accuracy and availability. It can provide a certain technical reference for the trajectory design and fuel consumption estimation during the preliminary stage.]]></description>
<pubDate>2016/12/31 18:39:27</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[ZENG Kui, GENG Yunhai and XIE Chengqing]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>ZENG Kui, GENG Yunhai and XIE Chengqing</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201606013]]></guid><cfi:id>278</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Dynamic characteristics and influence factors analysis of reciprocating pump-fed propulsion system]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201606014]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In order to investigate the dynamic characteristics and influence factors of reciprocating pump, a modular model library of the RPFPS (reciprocating pump-fed propulsion system) was established. The modular model library was built  on the basis of lumped parameter approximation and the dynamic simulation of the work process for RPFPS was carried out on the basis of the AMESim system. The effects of initial pressure of accumulator, equivalent volume of pipeline under gas generator and number of nozzles on the dynamic characteristics of reciprocating pump were studied. Results have been obtained as follows: due to the bigger initial pressure of accumulator,  less time was used to start the reciprocating pump, but the regulation ability of accumulator was weaker; it would take  less time to start the reciprocating pump because of  larger equivalent volume of pipeline under gas generator, but it would also lead to the increase of pressure fluctuation; the greater the number of nozzles, the lower the pressure fluctuation in gas generator, and the more time of reciprocating pump to start because of the slower pressure increasing speed.]]></description>
<pubDate>2016/12/31 18:39:27</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[NIE Yao<sup>1</sup>, CHENG Yuqiang<sup>1</sup>, WU Jianjun<sup>1</sup> and LI Shiliang<sup>2</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>NIE Yao<sup>1</sup>, CHENG Yuqiang<sup>1</sup>, WU Jianjun<sup>1</sup> and LI Shiliang<sup>2</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201606014]]></guid><cfi:id>277</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Anti-rendezvous evasive maneuver method considering space geometrical relationship]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201606015]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[An anti-rendezvous evasion maneuver method was proposed in order to escape from the spacecraft that has autonomous approaching ability. A bearing-only relative navigation model was built and the definition of absolutely non-observable maneuver was proposed. After some algebra, it was proved that the absolutely non-observable maneuver is non-existent. Based on that, an object function using vector multiplication was designed to find the minimum of measurement difference during the evasion. An optimization model was established and the variable bound was given so that the minimum of the object function could be obtained by the Genetic Algorithm. The numerical simulation was conducted with different maneuver impulse. The result shows that the proposed method can minimize the measurement difference between  evasive maneuver adopted and evasive maneuver ignored. The method presented offers a new viewpoint for evasion maneuver research.]]></description>
<pubDate>2016/12/31 18:39:27</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[YU Dateng, WANG Hua and ZHOU Wanmeng]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>YU Dateng, WANG Hua and ZHOU Wanmeng</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201606015]]></guid><cfi:id>276</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Effect of compressive sensing sparse reconstruction on star image]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201606016]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The sparse reconstruction is one of the key factors in compressive sensing theory. In order to apply sparse reconstruction to compressive imaging process of star tracker in an effective way, the effect of sparse reconstruction on star image was analyzed from the perspectives of star image error and star feature error. For the problem of image error, PSNR（peak signal-to-noise ratio） evaluation index was employed to observe reconstruction quality of star image under different reconstruction algorithm and diverse compression ratio. For the problem of feature error, firstly, the influential mechanism of sparse reconstruction on star feature was analyzed theoretically; and then the evaluation index of reconstruction error of star feature was proposed to investigate the reconstruction error of star centroid, brightness and number. Result shows that, the star image can obtain higher reconstruction quality than the common image with the same reconstruction condition under diverse compression ratio of selected algorithm, and the reconstructed star can keep its features for attitude determination to a large extent. The conclusion proves the validity of attitude estimation by using the reconstructed star image, verifies the feasibility of applying compressive sensing to star tracker and provides the practical foundation for compressive imaging of star tracker.]]></description>
<pubDate>2016/12/31 18:39:27</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[YIN Hang, YAN Ye and SONG Xin]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>YIN Hang, YAN Ye and SONG Xin</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201606016]]></guid><cfi:id>275</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Effect of Mars rarefied atmospheric dynamic error during aerobraking]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201605011]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Aimed at the problem which Mars can rarefy atmospheric dynamic errors that caused by seasonal variations and diurnal changes during Mars areobraking, the orbital dynamic equation including aerodynamic force was established. Through the research of aerodynamic parameter calculation method applied to rarefied flow, the effect of dynamic errors on aerodynamic force and aerobrake result was analyzed. In consideration of the application in Mars exploration, the characteristics of aerodynamic and orbit during Mars aerobraking were simulated under the condition that the atmospheric dynamic errors exist. To assure the safety of spacecraft and the aerobraking duration, the corridor of aerobraking and the requirement of navigation were proposed. The result can be a reference for the aerobraking implementation of future Chinese Mars exploration.]]></description>
<pubDate>2016/11/8 9:36:43</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[FANG Baodong<sup>1,2,3</sup>, WU Meiping<sup>1</sup> and ZHANG Wei<sup>2,3</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>FANG Baodong<sup>1,2,3</sup>, WU Meiping<sup>1</sup> and ZHANG Wei<sup>2,3</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201605011]]></guid><cfi:id>274</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Semi-physical simulation system design for attitude determination and control of micro/nano-satellite]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201605012]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Attitude control system requires special working environment, so it is hard to actualize on the ground, which has brought a certain reliability risk to satellite. According to the characteristics of micro/nano-satellite, a set of semi-physical simulation system for attitude determination and control was designed and implemented. A digital model simulated the satellite attitude and orbit motion, a sensor model generated the measured data, an actuator model generated the control torque, a sensor simulator realized the communication protocol and finally this system realized the whole simulation of attitude control system. The system can be connected in the satellite control system loop to assess software and hardware of the attitude control system, and to verify the performance of the algorithm. The system was applied to validate the attitude control system of TianTuo-3 in ground simulation. The comparison with the on-orbit test data shows that the design of system is reasonable and the result of simulation is credible.]]></description>
<pubDate>2016/11/8 9:36:44</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[SHENG Tao, BAI Yuzhu, HE Liang, RAN Dechao and ZHAO Yong]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>SHENG Tao, BAI Yuzhu, HE Liang, RAN Dechao and ZHAO Yong</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201605012]]></guid><cfi:id>273</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Motion modeling, mechanism analysis and trajectory optimization for dynamic soaring]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201605013]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Albatrosses use a flight manoeuvre which is called the dynamic soaring, to gain energy from horizontal wind gradient so as to travel for a very long journey and the period almost goes on without making stopovers or flapping their wings. Dynamic soaring is considered a promising technique which can be widely applied to UAV (unmanned aerial vehicle) for extending mission capabilities. The EOM (equation of motion) of a small UAV in the gradient wind field was derived and simplified in the airpath frame of axes based on the flight dynamics. According to the theorem of kinetic energy and mechanical energy variation with respect to the noninertial frame of reference respectively, the energygain mechanism during dynamic soaring was analyzed by using the simplified EOM. The differential flatness method was employed to solve loiter pattern and travel pattern trajectories for the objective function of minimum average change rate of control inputs. The analysis result indicates that the upwind climb and downwind dive is the basic energygain ways of dynamic soaring. The optimal results show that the control inputs are smoothed，even the staged constant inputs to make the actual control simpler. In the optimization of loiter pattern，when the wind gradient is treated as a decision variable, the optimization process finds the optimal wind gradient in the range of ［0，0.5 s<sup>-1</sup>］ for the objective function. While in the optimization of travel pattern, the value of the objective function is monotonically decreasing in the same range. ]]></description>
<pubDate>2016/11/8 9:36:45</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LIU Duoneng, HOU Zhongxi, GUO Zheng, YANG Xixiang and GAO Xianzhong]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LIU Duoneng, HOU Zhongxi, GUO Zheng, YANG Xixiang and GAO Xianzhong</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201605013]]></guid><cfi:id>272</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Integrated guidance and control of hypersonic vehicle with fuzzy disturbance observer]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201605014]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[A three-dimensional IGC (integrated guidance and control) approach based on fuzzy disturbance observer was proposed to take advantage of the coupling between the centroid motion, and the attitude motion, and of the uncertainties of a hypersonic vehicle in dive phase as well. An IGC model that can be applied to bank-to-turn control strategy was proposed according to the dynamic equations of the vehicle and the line-of-sight relative motion between the vehicle and the target. The uncertainties in the model were compensated by utilizing the fuzzy disturbance observer, and then an IGC approach was developed by using the block dynamic surface backstepping control method. The states of the closedloop system were proved to be uniformly ultimately bounded by adopting proper Lyapunov functions. Simulations show that the IGC method is robust to the uncertainties and satisfies the required performance. ]]></description>
<pubDate>2016/11/8 9:36:46</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[ZHAO Tun, WANG Peng, LIU Luhua and WU Jie]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>ZHAO Tun, WANG Peng, LIU Luhua and WU Jie</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201605014]]></guid><cfi:id>271</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Condenser parameters optimization in solar thermal propulsion system]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201605015]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[An advanced genetic algorithm was used to make an optimization analysis on the solar thermal propulsion system condenser parameters for reducing the mass of system. Considering the sunlight collection efficiency and the mass of condenser as the optimization objective function, a mathematical model of condenser work was established and several related simulation researches were carried out. The simulation results show that the advanced genetic algorithm can be effectively used in the optimization analysis of the sunlight collection efficiency and the condenser mass.]]></description>
<pubDate>2016/11/8 9:36:46</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[HUANG Minchao and WU Shang]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>HUANG Minchao and WU Shang</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201605015]]></guid><cfi:id>270</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Adaptive tracking guidance method in injection phase forhypersonic glide vehicles]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201605016]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[According to the trajectory tracking problem of hypersonic glide vehicle under great deviation conditions, a new adaptive tracking guidance method in the injection phase was put forward based on the adaptively revised weighting matrix. The main control mode and standard trajectory characteristics were analyzed. The simplified longitudinal motion equations were linearized near the standard trajectory. An improved adaptive tracking guidance method was designed by introducing the error term in linear quadratic performance index. The simulation results of CAV-H indicate that this method can achieve a great performance in adaptive tracking guidance in the injection phase, and has a good robustness to the initial and process deviation.]]></description>
<pubDate>2016/11/8 9:36:47</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[HE Ruizhi<sup>1</sup>, LIU Luhua<sup>1</sup>, TANG Guojian<sup>1</sup> and BAO Weimin<sup>1,2</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>HE Ruizhi<sup>1</sup>, LIU Luhua<sup>1</sup>, TANG Guojian<sup>1</sup> and BAO Weimin<sup>1,2</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201605016]]></guid><cfi:id>269</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Aerodynamic interference investigation of supersonic cluster munition dispensed by sequence]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201605017]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In order to analyze the multi-body flow characteristics and the aerodynamic interference characteristics for the sub-munitions in different bays under sequential separation,   the three-dimensional unsteady flow field of the cluster munition under two types of sequential separation and single separation style was simulated with the use of the unstructured dynamic mesh method, based on the governing equations of fluid dynamics and rigid body motion equations of 6DOF (degree of freedom). The variation of the flow characteristics and the aerodynamic interference characteristics of sub-munitions in different separation styles was shown and the interaction process of aerodynamic interference between the sub-munitions in different separation stages was revealed as the results. Numerical simulation results show that the flow characteristics become more complicated and the aerodynamic separation parameters of the rear sub-munition become lower than that of the front sub-munition because of the shock wave interaction between the sub-munitions in the process of sequential separation. During the short sequential separation, the interference from the front sub-munition to the rear sub-munition is more severe so that the security of the separation between the sub-munitions is affected.]]></description>
<pubDate>2016/11/8 9:36:48</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[WANG Jinlong, WANG Hao, JIANG Kun, TAO Ruyi and WANG Zhengwei]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>WANG Jinlong, WANG Hao, JIANG Kun, TAO Ruyi and WANG Zhengwei</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201605017]]></guid><cfi:id>268</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Coupled calculation of aerodynamic heating for hypersonic vehicle in rarefied flow]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201605018]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[A coupling method was presented to deal with the heating problems of hypersonic vehicles in rarefied flow. The DSMC (direct simulation Monte Carlo) method was combined with the heat conduction equation by introducing the Newton cooling law. An efficient loose coupling procedure which can calculate the aerodynamic heat and structure heating of vehicle configuration was designed to simulate the temperature distribution of thermal protection systems. After taking the blunted cone as an example to validate the DSMC code, a numerical experiment was conducted to simulate the structure temperature and heat flux distribution characteristics of the X37B orbital vehicle shape in cruise state. The results show that the presented coupling method can simulate the aerodynamic heating process of a hypersonic vehicle in rarefied flow, and can provide technical support for the design of rarefied-flow hypersonic vehicles in terms of thermal protection systems and aerodynamic heating characteristics analysis.]]></description>
<pubDate>2016/11/8 9:36:49</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[QU Cheng and WANG Jiangfeng]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>QU Cheng and WANG Jiangfeng</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201605018]]></guid><cfi:id>267</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[SAR positioning method based on high-precision scene matching]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201605019]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[A SAR platform location method which utilizes the high-precision scene matching of SAR images and optical reference images was proposed. According to that the projections of SAR platform and object point in SAR image centerline are collinear, some points on the centerline were equably engaged as control points in the proposal method, and then the spatial position was obtained by matching with optical reference image. The equation of the projection line on the local horizon of centerline was estimated with the points. The projection point position of the SAR platform on the horizontal plane was calculated by making use of the straight line and slant-range-altitude information, as well as the spatial position of the platform. Considering the difference between boresight and squint imaging mode, rough rectifying methods were respectively proposed according to the two modes to improve the matching precision. The impact of different errors on location precision was also analyzed and the precision estimation formulas were derived. Both simulation and real data test results show high accuracy and precision of the proposed method, thus bringing forth good practical value for engineering.]]></description>
<pubDate>2016/11/8 9:36:49</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[CHEN Shengyi<sup>1,2</sup>, LIU Xiaochun<sup>1,2</sup>, TENG Xichao<sup>1,2</sup>, LI Xiaoxue<sup>1,2</sup> and LEI Zhihui<sup>1,2</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>CHEN Shengyi<sup>1,2</sup>, LIU Xiaochun<sup>1,2</sup>, TENG Xichao<sup>1,2</sup>, LI Xiaoxue<sup>1,2</sup> and LEI Zhihui<sup>1,2</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201605019]]></guid><cfi:id>266</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Observability analysis for misalignments of inertial sensors in inertial platform self-calibration]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201605020]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[For the observability of inertial sensor misalignments in inertial platform self-calibration problem, the effects of the system model and platform coordinate frame on observability were analyzed. Based on different system dynamic models and measurement vectors, four system models were built. The observability of inertial sensors misalignments in different models with different definitions of platform coordinate frame was investigated. The theory conclusions and simulation results show that the system is observable only in two conditions: the system measurement models are built up with platform angles and accelerometer triad outputs, the system dynamic model is built up with platform angles and the platform coordinate frame should be defined with the benchmark hexahedron of platform; the system measurement models are built up only with accelerometers triad outputs, the system dynamic models are built up with platform attitude or misalignment models and the platform coordinate frame should be defined with the accelerometer sensor axes. ]]></description>
<pubDate>2016/11/8 9:36:50</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[DING Zhijian, CAI Hong and ZHANG Wenjie]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>DING Zhijian, CAI Hong and ZHANG Wenjie</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201605020]]></guid><cfi:id>265</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Deep convolutional neural network for motion compensated frame interpolation]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201605022]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In order to explore the application of deep learning theory in the problem of motion compensated frame interpolation, a DCNN (deep convolutional neural network) built with convolutional blocks and deconvolutional blocks was proposed. The proposed DCNN is capable of processing input images with different resolutions and preserving finegrained image details. The temporal coherent image sequences were used to construct the training sample and the stochastic gradient descent method was adopted to train the designed DCNN. Qualitative and quantitative experiments show that the trained DCNN obtains better interpolated images than the traditional approach in two testing images sequences.]]></description>
<pubDate>2016/11/8 9:36:52</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LONG Gucan<sup>1,2</sup>, ZHANG Xiaohu<sup>1,2</sup> and YU Qifeng<sup>1,2</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LONG Gucan<sup>1,2</sup>, ZHANG Xiaohu<sup>1,2</sup> and YU Qifeng<sup>1,2</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201605022]]></guid><cfi:id>264</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Applications of high-order weighted compact nonlinear scheme for thermo-chemical nonequilibrium flow]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201605026]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[High-order scheme has advantages in the simulations of complex flow for its good behavior of preserving high spatial resolution with lower cost than the second order methods. WCNS-E-5(weighted compact nonlinear scheme) was applied in the simulations of thermo-chemical nonequilibrium flow around a cylinder with the freestream velocity from 5 km/s to 5.7 km/s. The distribution of correct flow field parameter was acquired, the pressure and heat flux on the surface agreed well with the experimental data. WCNS-E-5 also exhibited better performance on the grid convergence of heat flux than the second order MUSCL scheme. Results show that the present attempt to combine high order scheme with the calculations of stiff chemically reacting flow is basically successful, and it has established a good foundation for the further study.]]></description>
<pubDate>2016/11/8 9:36:55</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[GE Mingming, ZENG Ming and ZHAO Xiaoyu]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>GE Mingming, ZENG Ming and ZHAO Xiaoyu</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201605026]]></guid><cfi:id>263</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Application of fifth-order accurate HWCNS for low-speed complex flow field]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201604001]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The fifth-order accurate explicit HWCNS(hybrid cell-edge and cell-node weighted compact nonlinear schemes) was used to solve Reynolds averaged NavierStokes equations. The grid convergence study of 30P-30N was performed by generating multi-block structured grids. The effects of HWCNS and the secondorder accurate MUSCL on pressure distribution and velocity profiles at typical stations were studied using SA turbulence model without regarding transition, furthermore the numerical and experimental results were compared and analyzed. The trapezoidal wing was numerically simulated using HWCNS and SA turbulence model, and the application performance of HWCNS for low-speed complex configuration flows was discussed by analyzing the aerodynamic characters and the pressure distribution.Simulation results indicate that the pressure distribution of 30P-30N is simulated with the fully turbulent model accurately; as for the trapezoidal wing, HWCNS shows good simulation performance when dealing with the attached flow and small flow separation.]]></description>
<pubDate>2016/9/13 11:24:52</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[ZHOU Yunlong<sup>1</sup>, LIU Wei<sup>1</sup>, DONG Yidao<sup>1</sup>, WANG Guangxue<sup>1,2</sup> and DENG Xiaogang<sup>1</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>ZHOU Yunlong<sup>1</sup>, LIU Wei<sup>1</sup>, DONG Yidao<sup>1</sup>, WANG Guangxue<sup>1,2</sup> and DENG Xiaogang<sup>1</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201604001]]></guid><cfi:id>262</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Numerical simulation on VFE-2 rounded leading edge delta wing using weighted compact nonlinear scheme]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201604002]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In order to evaluate the influence of transition on the vortex structure of delta wing, a numerical simulation of VFE-2 rounded leading edge delta wing was carried out by using a high-order scheme-weighted compact nonlinear scheme and the γ－Re<sub>θ</sub> transition model. A comparisons between calculated results and experiment data indicate that the leading edge vortex begins at a certain distance of the wing apex and the transition has great influence on the onset of leading edge vortex. Using turbulence model without transition, the leading edge separation is delayed much, while with transition model the calculated results show a good agreement with experiment data. With transition model, numerical simulation on VFE-2 rounded leading edge delta wing at variation of the angle-of-attack was carried out. The calculated results which agree well with experiment data show that at a low angle-of-attack, there is no separation-induced leading-edge vortex, but with the increase of angle-of-attack the leading edge separation displays being closer to the trailing edge and moves upstream.]]></description>
<pubDate>2016/9/13 11:24:52</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[WANG Guangxue<sup>1,2</sup>, WANG Shengye<sup>1</sup>, WANG Dongfang<sup>1</sup> and DENG Xiaogang<sup>1</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>WANG Guangxue<sup>1,2</sup>, WANG Shengye<sup>1</sup>, WANG Dongfang<sup>1</sup> and DENG Xiaogang<sup>1</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201604002]]></guid><cfi:id>261</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Calibration and application of γ－Re<sub>θ</sub> transition model based on high-order weighted compact nonlinear scheme]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201604003]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In order to accurately simulate the transition in aeronautical engineering, the low speed flat plate data was adopted for the calibration of γ－Re<sub>θ</sub> transition model based on high-order WCNS (weighted compact nonlinear scheme) on the platform of high-order numerical wind tunnel. Based on the calibrated transition model, the flow over the low speed airfoil was investigated. Comparison between the calculated results and the experiment data indicates that the γ－Re<sub>θ</sub> transition model based on WCNS can predict the location of nature transition, bypass transition or separation transition very well and has low mesh sensitivity; only the transition model can calculate the drag coefficient accurately within a moderate Reynolds number range where the length of the laminar flow region is comparable to that of the turbulent flow region.]]></description>
<pubDate>2016/9/13 11:24:52</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[WANG Shengye<sup>1</sup>, WANG Guangxue<sup>1,2</sup>, DONG Yidao<sup>1</sup> and DENG Xiaogang<sup>1</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>WANG Shengye<sup>1</sup>, WANG Guangxue<sup>1,2</sup>, DONG Yidao<sup>1</sup> and DENG Xiaogang<sup>1</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201604003]]></guid><cfi:id>260</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Influence of ducted fan profile parameters on aerodynamic characteristics]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201604005]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The influence of ducted fan profile parameters to aerodynamic characteristics was investigated. The threedimensional incompressible viscous NavierStokes equations and SST k-ω turbulence model were used to simulate the complex flow of a 2-blade propeller, which was based on the sliding mesh method. To demonstrate the feasibility of the method, the result was compared with the experimental data. The influences of the lip shape, diffuser angle, the height of duct on aerodynamic characteristics and the flow field were analyzed under the condition of hovering and within the limits of 3000 r/min to 8500 r/min. The thrust coefficient was produced by the ducted fan under the condition that the elliptical lip is smaller than the others, and its aerodynamic efficiency is very low. The power coefficient is the smallest when the diffuser angle is 8.2°. The flow separation emerges nearer to the duct under the propeller disk, with the increase of diffuser angle. The sensitivity of thrust coefficient to the change of ducted fan height is low. The power coefficient descends slightly with the increase of height.]]></description>
<pubDate>2016/9/13 11:24:52</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LI Xiaohua, GUO Zheng, LIU Zhaowei and CHEN Qingyang]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LI Xiaohua, GUO Zheng, LIU Zhaowei and CHEN Qingyang</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201604005]]></guid><cfi:id>259</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Three-dimensional flat-plate boundary layers generated by two swept shock waves of the same side]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201604006]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In order to seek a sidewall compression method to weaken the interaction between swept shock waves of the same side and boundary layers, the three-dimensional flatplate boundary layer generated by the interaction of two swept shock waves of the same side and the flat-plate boundary layer was numerically studied. The flow mechanism of this three-dimensional boundary layer was analyzed. Also, the three-dimensional boundary layer was quantitatively compared with the one generated by one swept shock wave which has the same flow deflection angle. The results show that, in the case of two swept shock waves, the first swept shock wave makes the boundary layer next to the sidewall thinner, so the interaction between the second shock wave and the boundary layer in the attachment region becomes weaker, leading to the total effect that the interaction between two shock waves and the boundary layer is weaker than that at the one swept shock wave case; the total flow deflection angle of two swept shock waves is the same as one shock wave case, so the strength of the converged shock wave is essentially the same; the three-dimensional boundary layer generated by the swept shock is still conical, and the angle between the separation line and the inflow is essentially the same with the one swept shock case.]]></description>
<pubDate>2016/9/13 11:24:52</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[HE Gang and ZHOU Jin]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>HE Gang and ZHOU Jin</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201604006]]></guid><cfi:id>258</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Analysis and improvement of weights in WENO schemes]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201604007]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In order to improve the computational performance of the WENO scheme, a new WENO scheme, namely WENO-E scheme was constructed, which reduces dissipation close to discontinuities. Based on the analysis of the algorithm for weighted factors in the classical WENO scheme (namely WENO-JS) proposed by Jiang and Shu, the new scheme was constructed by introducing indirect smooth indicator. Theoretical analysis shows that the WENO-E scheme can reach the same convergence order of WENO-JS with the same computational efficiency; while it can obtain smaller truncation errors at smooth parts of the solution and higher resolution close to the discontinuities with the same grids than the WENOJS. Subsequently, compared with the classical WENO scheme, when numerical experiments with the linear transport equation, the nonlinear Burgers equation and the one dimensional Euler system of equations are conducted, the WENO-E scheme achieves better numerical solutions.]]></description>
<pubDate>2016/9/13 11:24:52</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[CHAI Delin, LI Yurun, SUN Zhongguo and XI Guang]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>CHAI Delin, LI Yurun, SUN Zhongguo and XI Guang</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201604007]]></guid><cfi:id>257</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Preliminary application of Reynolds stress model]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201604008]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[For the verification and validation of SSG/LRR-ωReynolds stress model, four typical two dimensional cases from NASA turbulence resources website were chosen, including zero pressure gradient flat plate, bump-in-channel, airfoil near-wake and flow over NACA0012 airfoil. A part of numerical results were in good agreement with that of CFL3D. For flow over NACA0012 airfoil, lift coefficients of Reynolds stress model and SA model were compared. It is obvious that near the stall angle of attack, Reynolds stress model has advantages over SA model. Based on these results, SSG/LRR-ωReynolds stress model was applied to the simulation of complex DLR-F6 wingbody configuration. Pressure coefficient in typical stations is comparable to that of experiment. Besides, small range of separation in the wing-body intersection is well captured. ]]></description>
<pubDate>2016/9/13 11:24:52</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[DONG Yidao<sup>1</sup>, WANG Dongfang<sup>1</sup>, WANG Guangxue<sup>1,2</sup> and DENG Xiaogang<sup>1</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>DONG Yidao<sup>1</sup>, WANG Dongfang<sup>1</sup>, WANG Guangxue<sup>1,2</sup> and DENG Xiaogang<sup>1</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201604008]]></guid><cfi:id>256</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Numerical simulation of hypersonic double cone flows with high-order methods]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201604009]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Hypersonic low enthalpy laminar flows of double cone with 25°/55°  geometry were simulated by using high-order WCNS (weighted compact nonlinear schemes), and their capabilities to accurately predict laminar shock wave/boundary layer interaction were examined. The simulations were performed through adopting the second order MUSCL, the third-order and the fifth-order WCNS as spatial discretization schemes, employing the secondorder dual time-stepping approach for time integration and using different flux functions, such as hybrid Roe-Rusnov, AUSMPW+ and Van Leer, for comparison. The effects of high-order methods on time and grid convergence, as well as the dissipation characteristics of flux functions, were analyzed. The numerical simulation results indicate that the highorder methods can obtain well-resolved results on coarse grid and eliminate the sensitivity of flux functions. However, the high-order methods need longer computational time to reach convergence. The computed results show good agreement with the experimental data, and the computational accuracy may be characterized as reasonable for most engineering purposes.]]></description>
<pubDate>2016/9/13 11:24:52</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[WANG Dongfang<sup>1</sup>, DENG Xiaogang<sup>1</sup>, WANG Guangxue<sup>1,2</sup> and LIU Huayong<sup>3</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>WANG Dongfang<sup>1</sup>, DENG Xiaogang<sup>1</sup>, WANG Guangxue<sup>1,2</sup> and LIU Huayong<sup>3</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201604009]]></guid><cfi:id>255</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Numerical analysis of the  tail cavity effect on  underwater vehicle hydrodynamic damping force]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201604010]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[For the influence of tail cavity on hydrodynamic damping force, a method was proposed by combing the rotating reference frames and cavity multiphase flow simulation techniques and solving the Reynolds averaged NS equations. Numerical research indicates that the unbalance of vehicle tail part pressure distribution has been relieved by tail cavity, which causes the reduction of hydrodynamic damping force. As the cavity expands, the decreasing rate trends tend to be slower. The tail cavity also changes the trend of damping force, which varies with the attack angle. Research reveals the necessary consideration of the effect of tail cavity on underwater vehicle hydrodynamic damping force design.]]></description>
<pubDate>2016/9/13 0:00:00</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[YOU Tianqing, WANG Zhanying, QUAN Xiaobo, BAO Wenchun, XIAO Lu and CHENG Shaohua]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>YOU Tianqing, WANG Zhanying, QUAN Xiaobo, BAO Wenchun, XIAO Lu and CHENG Shaohua</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201604010]]></guid><cfi:id>254</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Attitude control of dynamic scanning imaging satellite of control moment gyros]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201604019]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[According to the problem of attitude control of satellite dynamic scanning imaging, the dynamic model of the satellite attitude was built and the specific requirement of dynamic scanning imaging tasks for attitude control was analyzed. Combined with the dynamic scanning imaging tasks, a typically attitude maneuver scheme was designed. The required control moment of the process of dynamic scanning imaging was estimated. A pitching maneuver control law based on the expected torque and real-time attitude of satellite was developed, and the steering law of five pyramid configuration gyros was given. A numerical simulation was presented for the designed control law based on a maneuver task. The simulation results proved that the proposed scheme can satisfy the requirement of attitude control of dynamic scanning imaging satellite.]]></description>
<pubDate>2016/9/13 11:24:53</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[ZHAO Bolin, LIU Kun and ZHANG Li]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>ZHAO Bolin, LIU Kun and ZHANG Li</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201604019]]></guid><cfi:id>253</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Research on health simulation and evaluation for electric servo system based on parameter identification]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201604021]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[For the fact that the current fault diagnosis methods cannot detect soft fault effectively, a variable detection method based on electric servo system model was proposed for health simulation and evaluation. Common failures of electric servo system, such as motor module, controller and transmission mechanism were analyzed, and the mathematical models were built up for common health states. By injecting different health coefficients into the system, the characteristics of state variable were obtained, so the knowledge base was built up to locate the source of faults and to evaluate the changing trend of the failure parameter by health factors. Finally, the resistance of winding and the motor torque constant are chosen as health factors, the feasibility of health factors estimation algorithm is verified by simulation.]]></description>
<pubDate>2016/9/13 11:24:53</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[ZHOU Weizheng<sup>1</sup>, LI Xuefeng<sup>1</sup> and ZENG Qinghua<sup>2</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>ZHOU Weizheng<sup>1</sup>, LI Xuefeng<sup>1</sup> and ZENG Qinghua<sup>2</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201604021]]></guid><cfi:id>252</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Multi-objective trajectory optimization for hypersonic glide vehicle using boundary intersection method]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201604022]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The trajectory design for hypersonic glider vehicle subject to complex constraints is a multi-objective trajectory optimization problem. A multi-objective trajectory optimization method combining the boundary intersection method and the pseudospectral method was proposed. The multi-objective trajectory optimization problem was established based on the analysis of the features of trajectory for hypersonic glider vehicle. The multiobjective trajectory optimization problem was translated into a set of general optimization sub-problems by using the boundary intersection method and pseudospectral method. The sub-problems were solved by nonlinear programming algorithm. In the method, the solution that has been solved was employed as the initial guess for the next sub-problem. The maxima cross range and minimal peak heat problem was solved by the proposed method. The numerical results demonstrate that the proposed method can obtain the Pareto front of the optimal trajectory, which can provide  reference for the trajectory design for hypersonic glider vehicle.]]></description>
<pubDate>2016/9/13 11:24:53</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[WANG Lei, GE Jianquan, YANG Tao, FENG Zhiwei and LI Zhengnan]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>WANG Lei, GE Jianquan, YANG Tao, FENG Zhiwei and LI Zhengnan</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201604022]]></guid><cfi:id>251</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Ballistic correction guidance law based on the control of velocity direction]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201604023]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Taking the limited control authority and guidance information of a gun-launched guided projectile into account, a novel three-dimension terminal guidance law based on the combination of the correction of the velocity direction via impact point prediction and continuous distribution of acceleration command was proposed. The deviations between the impact point of the projectile and the target were predicted on the basis of the series solutions of the nonlinear ballistic equations. According to the deviations, two methods to calculate the direction angle corrections of the current speed were addressed. The remaining flight time was designed as the correction time. The acceleration correction formulas were established through sharing the direction angle corrections of the current speed into the whole remaining guided flight to reduce the possibility of command saturation. By predicting the impact point and distributing the acceleration corrections continuously, the trajectory was shaped in real time. The simulation results show that the proposed guidance law is feasible and effective, and provides the performances of high precision with little requirements of control authority, and has great guidance and damage effects, which can provide reference for the application of the guided projectile.]]></description>
<pubDate>2016/9/13 11:24:54</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[XU Qiuping, WANG Zhongyuan and CHANG Sijiang]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>XU Qiuping, WANG Zhongyuan and CHANG Sijiang</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201604023]]></guid><cfi:id>250</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Equivalent compensation theory of the earth disturbance gravity  on ballistic missile hit accuracy]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201604024]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In order to eliminate the effect of the disturbance gravity and improve the hit accuracy of ballistic missile, the equivalent theory based on the characteristics on the movement of ballistic missile and control system theory was established to compensate the effect of the earth disturbance gravity on motion parameters indirectly and meet the hit accuracy requirement. According to the characteristics of different compensation modes and compensation quantity, the compensation modes of embedded mode, fractional step mode and sectional mode, etc. were proposed, which provides a general framework and theoretical basis for compensating the influence of disturbance gravity to the movement of ballistic missile.]]></description>
<pubDate>2016/9/13 11:24:54</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[MA Baolin, ZHANG Hongbo, ZHENG Wei and WU Jie]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>MA Baolin, ZHANG Hongbo, ZHENG Wei and WU Jie</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201604024]]></guid><cfi:id>249</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Particle swarm optimization method for impulse-correction projectiles]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201604025]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[According to the discontinuous characteristics of impulse correction projectile, a class of parameters optimization method for its control system was presented. Considering the two requirements of the correction cost and precision of impulse thrusters, the minimum amount of numbers of impulse thrusters and the control miss-distance were taken as a double-objective function, and it was put forward to select the time interval between the two neighboring impulse forces as design variable in condition of wind disturbance. Based on this, a  modified particle swarm optimization algorithm was developed to improve the convergence speed of this optimization process. The simulation result indicates that the presented optimization algorithm can obtain the optimal solution efficiently, which provides a reference approach to find the optimal impulse correction parameters and work modes under wind disturbance.]]></description>
<pubDate>2016/9/13 11:24:54</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[SUN Ruisheng<sup>1</sup>, HONG Qiao<sup>1</sup>, CHEN Jinzhang<sup>1</sup> and SUN Chuanjie<sup>2</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>SUN Ruisheng<sup>1</sup>, HONG Qiao<sup>1</sup>, CHEN Jinzhang<sup>1</sup> and SUN Chuanjie<sup>2</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201604025]]></guid><cfi:id>248</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Scalar transport and diffusion study progress of supersonic mixing layer with high Reynolds number]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201604026]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[For the problem of  the application of the scalar mixing of supersonic mixing layer in the combined cycle engine, the study progress of the supersonic mixing layer and the scalar mixing process in the supersonic mixing layer both at home and abroad was summarized. Then the methods for counteracting the shortcomings of the study on scalar transport and diffusion characteristics of supersonic mixing layer with high Reynolds number were proposed. Finally, some directions being worth studying deeply in the field were pointed out.]]></description>
<pubDate>2016/9/13 11:24:54</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[SHEN Chibing<sup>1,2</sup>, SHI Shaoping<sup>3</sup> and FENG Junhong<sup>1,2</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>SHEN Chibing<sup>1,2</sup>, SHI Shaoping<sup>3</sup> and FENG Junhong<sup>1,2</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201604026]]></guid><cfi:id>247</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Experimental investigation on fracture toughness of metal foam]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201604027]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In practical applications, fracture properties and fracture toughness of porous metal foam for bearing are very important. Based on ASTM standards, three-point bending of aluminum foam samples was used to determine I type fracture toughness. It is shown that the fracture of metal foam is brittle fracture. The deformation is localized in the thinnest regions of the cell walls surrounding the crack tip. With further loading, some cell walls existed fracture phenomenon and microcracks appear in the vicinity of the crack tip. With the increasing of load a main crack is initiated at the notch root or at the pre-crack by a coalescence of microcracks, and starts to propagate through the cell structure. The crack follows the weakest path through the structure and creates the secondary cracks and crack bridges. The main way of crack extension is I type fracture. According to the P-V curve characteristics, taking the force and displacement of the maximum load point to calculate the critical crack tip opening displacement, the average cracktip opening displacement is 0.051mm.]]></description>
<pubDate>2016/9/13 11:24:54</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[WANG Xinzhu<sup>1,2,3</sup>, ZHOU Xiong<sup>3</sup>, ZHU Bingjie<sup>4</sup> and PENG Xianghe<sup>3</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>WANG Xinzhu<sup>1,2,3</sup>, ZHOU Xiong<sup>3</sup>, ZHU Bingjie<sup>4</sup> and PENG Xianghe<sup>3</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201604027]]></guid><cfi:id>246</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Numerical simulation on finite mass inflation dynamics of parachute]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201604029]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In order to study the finite mass inflation dynamic behavior of parachute at an airdrop mission, the penalty coupling algorithm and the adaptive mesh technology were used to analyze the fluid-structure interaction characteristics between the flexible parachute structure and the surrounding incompressible flow field. The three dimensional dynamic opening profiles of parachute were numerically simulated and some parameters of parachute system like dropping velocities and drag coefficients were obtained; the influences of initial dropping velocity on filling time and drag area were compared; the trajectory was validated by the experimental data from airdrop tests. The computation results show that this method can efficiently simulate the dynamic characteristics of finite mass inflation in parachute system. The simulation results coincide with the test results.]]></description>
<pubDate>2016/9/13 0:00:00</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[GAO Xinglong<sup>1,2</sup>, ZHANG Qingbin<sup>1</sup>, GAO Qingyu<sup>1</sup>, TANG Qiangang<sup>1</sup> and YANG Tao<sup>1</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>GAO Xinglong<sup>1,2</sup>, ZHANG Qingbin<sup>1</sup>, GAO Qingyu<sup>1</sup>, TANG Qiangang<sup>1</sup> and YANG Tao<sup>1</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201604029]]></guid><cfi:id>245</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Design of any-order direct digital synthesizer for high-dynamic GNSS signal Doppler simulation]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201603002]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In order to accurately simulate the Doppler characteristics of high dynamic GNSS signals, a method for designing any-order DDS (direct digital synthesis) signal synthesizer was proposed. An any-order DDS synthesizer structure was designed; a formula for calculating the initial phase of every accumulator in DDS synthesizer was derived by using theoretical analysis; a technique to determine the DDS word length was developed. Finally, the simulation accuracy of the proposed method for the Doppler characteristics of GNSS signals was validated through simulations. In addition, since the proposed method for designing DDS synthesizer has no order limitation, it can be widely used in different types of signal simulators.]]></description>
<pubDate>2016/7/7 11:13:54</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[ZHOU Chao, WANG Yueke, QIAO Chunjie and DAI Weihua]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>ZHOU Chao, WANG Yueke, QIAO Chunjie and DAI Weihua</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201603002]]></guid><cfi:id>244</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Construction method of guide star catalog for SINS/CNS]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201603011]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Building a guide star catalog which has the characteristics of completeness, simplicity and query rapidity is an important prerequisite and guarantee to realize the SINS/CNS(strapdown inertial navigation system/celestial navigation system). The Tycho-2 catalog in astronomy was selected as the initial catalog of the guide star catalog.  The ball rectangle partition method  was improved on the basis of the Tycho-2 catalog. It included how to divide the partition and the sub partition. The selection strategy of the alternative guide star was also creatively proposed. The experimental results show that the number of the alternative guide stars using the improved ball rectangle partition method most accounts for 19.37% of the guide stars used for the declination zone method and only accounts for 3.12% of the guide stars used for the traverse method. Therefore, the improved ball rectangle partition method is more accurate and rapid, and is more suitable for the strapdown inertial navigation system/celestial navigation system.]]></description>
<pubDate>2016/7/7 11:14:07</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[MA Baolin, WU Jie and ZHANG Hongbo]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>MA Baolin, WU Jie and ZHANG Hongbo</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201603011]]></guid><cfi:id>243</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Influence of nozzle structure on high pressure water jet and optimization design of nozzle structure parameter]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201603012]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Nozzle is the crucial component used to generate high pressure water jet, and its structure form has large influence on dynamic performance of high pressure water jet. So the influence of nozzle structure on high pressure water jet was analyzed, and the optimization design of nozzle structure parameter was implemented. A two-phase flow computational fluid dynamics model was employed to analyze the flow field. 〖HJ*2〗The Kriging surrogate model was used to replace the computational fluid dynamics model in the process of optimization design for reducing the computational resources. The nondominated sorting genetic algorithm and multiobjective evolutionary algorithms based on decomposition were respectively employed to carry out single and multi objective optimization design. The research results show that the general capability of lineform nozzle is the best, the concavity-form nozzle is in the middle, and the protrudingform nozzle has the worst capability. The single and multi objective optimization design of lineform nozzle is implemented, in which the core zone length and the mass flux of water jet are taken as optimization objectives. Compared with the baseline, the two indexes increased by 14.71% and 27.56% respectively after the single objective optimization. The optimal semi-cone angle after multi objective optimization located on ［15.4°， 89.8 °］. The global optimization algorithm based on surrogate model and evolutionary algorithm is proved to be effective.]]></description>
<pubDate>2016/7/7 11:13:51</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[HAN Qilong and MA Yang]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>HAN Qilong and MA Yang</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201603012]]></guid><cfi:id>242</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Landing footprint generation of entry vehicle based onGauss pseudospectral method]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201603013]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[To reduce calculation time and improve optimization result, a Gauss pseudospectral method was proposed. For the attack angle was regarded as a state variable and only bank angle was optimized, which was reasonable since attack angle profile was often predesigned in engineering. Down-range of vehicle was regarded as event constraint to obtain the maximum cross-range, while the flight path angle was regarded as path constraint to eliminate skips on the trajectory. Through simulation, the footprint of CAV(common aero vehicle) is generated, which is in accordance with the theoretical analysis of the indirect optimization method.]]></description>
<pubDate>2016/7/7 11:14:08</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[WANG Tao<sup>1</sup>, ZHANG Hongbo<sup>1</sup>, LI Yongyuan<sup>2</sup> and TANG Guojian<sup>1</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>WANG Tao<sup>1</sup>, ZHANG Hongbo<sup>1</sup>, LI Yongyuan<sup>2</sup> and TANG Guojian<sup>1</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201603013]]></guid><cfi:id>241</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[High-accuracy state propagation of non-cooperative relative orbit in space]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201603014]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In order to resolve the problem of relative navigation during the course approaching a non-cooperative space target, a highly accurate state propagation model of non-cooperative relative orbit motion was proposed on the basis of  the relative orbit dynamics equations and the second order Runge-Kutta formula. Taking the J<sub>2</sub> perturbation into account and expanding the target orbit equations into second order Taylor series beside the reference orbit, the angular velocity and the angular acceleration of reference orbit were further deduced and the relative orbit dynamics differential equation was built. After giving the initial value, the second order Runge-Kutta method was used to propagate the relative orbit motion. With the use of numerical integral method, the model can be widely used without any limited condition in relative orbit dynamics model forms; with the use of second order Runge-Kutta method, the computing efficiency is improved while the calculation accuracy is guaranteed. Two simulation scenarios, a low Earth orbit scenario and a high Earth orbit scenario, were designed to testify the generality and precision.]]></description>
<pubDate>2016/7/7 11:14:09</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[ZHU Zhenglong, YAN Ye and YANG Yueneng]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>ZHU Zhenglong, YAN Ye and YANG Yueneng</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201603014]]></guid><cfi:id>240</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Dynamics modeling and analysis of on-orbit refueling assembled spacecraft]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201603015]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[A research was presented to solve the problem of dynamics modeling and characteristics analysis in the case of the mass distribution of the spacecraft changes obviously during the on-orbit propellant refueling process. The variable-mass vehicle was considered to consist of two parts: a rigid platform and the liquid propellant confined in tanks. The liquid in tanks was regarded as a finite number of lumped masses with time-varying mass, configuration and position, so that, the actual physics could be abstracted as a set of variable mass particles with fixed border. Then, the dynamics model of refueling spacecraft was established by using the general equations of mass-varying particles set. Based on some reasonable assumptions about the structure of vehicle, the misalignment moment and the reactive force were eliminated from equations. It is remarkable that the established model include time-varying parameters and damping terms. Besides, the dynamics characteristics of the model were analyzed by using the Lyapunov′s stability criterion. Simulation results demonstrate that the difference structure of the vehicle effect the state trajectories dramatically, and prove that theoretic analysis is correct.]]></description>
<pubDate>2016/7/7 11:14:10</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[YANG Yajun, LIAO Ying and WEN Yuanlan]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>YANG Yajun, LIAO Ying and WEN Yuanlan</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201603015]]></guid><cfi:id>239</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Robust flight control based on generalized extended state observer]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201603016]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The robust flight control based on the generalized extended state observer was investigated to address the problems of parameter uncertainties, external disturbances and flight control with measurement noise. The nonlinear longitudinal dynamics were transformed into the linear-like structure state-space equations of state-dependent coefficients on the basis of the state-dependent Riccati equation control method. According to the control method based on generalized extended state observer, the disturbance compensation gain was designed to estimate and attenuate the external disturbances. Consequently, the state feedback gain and disturbance compensation gain were derived to track the desired angle of attack by solving the state-dependent coefficients and the algebraic Riccati equation on-line. Compared with other control methods, the proposed approach not only is robust with the parameter uncertainties and external disturbances, but also remains perfect in tracking performance with the measurement noise. It has high engineering application value.]]></description>
<pubDate>2016/7/7 11:14:12</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[ZHANG Yinhui, YANG Huabo, JIANG Zhenyu and ZHANG Weihua]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>ZHANG Yinhui, YANG Huabo, JIANG Zhenyu and ZHANG Weihua</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201603016]]></guid><cfi:id>238</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Numerical investigation of water-exit cavitation flow of submarine-launched missile]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201603027]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Based on Zwart-Gerber-Belamri cavitation model, a numerical calculation method of cavity flow of water-exit missile with complex configuration was proposed, in which the technology of dynamic mesh and composite mesh was used. Cavitation formation, evolvement and influence of shoulder, rudder and protuberance of water-exit missile were analyzed. The simulation results acclaim that in the beginning of water-exit course, body-attached bubble quickly grows due to reduction of cavitation number. After that, the effect of bubble break-off and oscillation becomes more obvious. The cavitation of shoulder firstly appears at the water-exit speed of 15 m/s. And it grows quickly with water-exit speed. The dissymmetry of shoulder cavitation becomes obvious in the attack angle of 5°～10°. The cavitation of rudder is hardly influenced by waterexit speed. The proportion of cavitation area of rudder is less than 10% when the  attack angle is less than 5°, and rapidly increases to 50% when the attack angle beyond 5°. Reduction of protuberance size is beneficial to cavitation avoidance. The influence of the  attack angle on protuberance cavitation is unapparent. Protuberance can induce the cavitation on nearby missile body at high speed.]]></description>
<pubDate>2016/7/7 0:00:00</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[ZHANG Chongxian, LI Xianglin and LIU Yuqiu]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>ZHANG Chongxian, LI Xianglin and LIU Yuqiu</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201603027]]></guid><cfi:id>237</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Effects of cavity arrangement on characteristics of supersonic combustion of vaporized kerosene]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201602001]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Considering the two different cavity arrangement schemes, a series of direct-connected combustion tests were conducted with vaporized RP-3 under the simulated Mach 6.0 flight condition. Effects of cavity arrangement on characteristics of supersonic combustion of vaporized kerosene were investigated by comparing with the high-speed flame luminosity images, static pressure distributions along the combustor wall, and the thrust increments. The results show that the cavity arrangement and equivalence ratios affect the flame distribution, the heat release characteristic and the combustor performance significantly. For the parallel-cavity-equipped combustor, the flame distribution and heat release are concentrated near cavities, and the fuel specific impulse shows low sensitivity to the equivalence ratio. While the single-cavity-equipped combustor has a dispersive flame distribution and heat release, and the fuel specific impulse increases with the equivalence ratio.]]></description>
<pubDate>2016/5/6 16:32:20</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[ZHONG Zhan<sup>1,2</sup>, WANG Zhenguo<sup>1,2</sup> and SUN Mingbo<sup>1,2</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>ZHONG Zhan<sup>1,2</sup>, WANG Zhenguo<sup>1,2</sup> and SUN Mingbo<sup>1,2</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201602001]]></guid><cfi:id>236</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Statistical analysis of low frequency unsteady combustion of gas generator]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201602002]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In order to satisfy the demand of scramjet ground test, a gas generator was designed. Tests were taken to study the stability characteristics of combustion using the statistical approach. Results indicate that the proportion of unsteady combustion accounts for 32.7%. All unsteady combustion occurred belongs to low frequency oscillation. There are two kinds of oscillation forms. One has dominant frequency crest, which has low frequency combustion instability or chuffing. For the other one, there is no dominant frequency crest，namely rough combustion. The probability that rough combustion occurs is relatively high and it is related to the excess oxidizer coefficient, while the low frequency combustion instability occurs with lower probability. Result shows that the energy distribution of the two unsteady combustions is different. ]]></description>
<pubDate>2016/5/6 16:32:20</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[ZHANG Xinqiao<sup>1,2</sup>, LI Qinglian<sup>1,2</sup>, SHEN Chibing<sup>1,2</sup> and KANG Zhongtao<sup>1,2</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>ZHANG Xinqiao<sup>1,2</sup>, LI Qinglian<sup>1,2</sup>, SHEN Chibing<sup>1,2</sup> and KANG Zhongtao<sup>1,2</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201602002]]></guid><cfi:id>235</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Combustion characteristics of an extreme fuel-rich throttleable rocket engine]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201602003]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[To study the combustion characteristics of a rocket engine under continuous throttling, a continuous throttling experiment was conducted by using GOX(gaseous oxygen)/kerosene as propellants. Mass flow rate of kerosene was continuously throttled by a throttleable cavitation Venturi nozzle. Successful ignition under fuel rich condition (mixture ratio ranged from 0.405 to 0.690) and the continuous throttling of mixture ratio and combustion gas flow rate were achieved. Results show that chamber pressure increases with the decrease of kerosene flow when the mixture ratio is less than 0.535 but decreases when the mixture ratio is greater than 0.535. Meanwhile, characteristic velocity and combustion efficiency increase with the increasing mixture ratio, but the increasing ratio is bigger when the mixture ratio is less than 0.535 than that when the mixture ratio is greater than 0.535. The results indicate that the mass flow rate of propellants and combustion efficiency simultaneously affect the chamber pressure. Combustion efficiency dominates the chamber pressure when the mixture ratio is less than 0.535 while mass flow rate of propellants dominates when the mixture ratio is greater than 0.535.]]></description>
<pubDate>2016/5/6 16:32:20</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[CHENG Peng<sup>1,2</sup>, LI Qinglian<sup>1,2</sup>, ZHANG Xinqiao<sup>1,2</sup> and KANG Zhongtao<sup>1,2</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>CHENG Peng<sup>1,2</sup>, LI Qinglian<sup>1,2</sup>, ZHANG Xinqiao<sup>1,2</sup> and KANG Zhongtao<sup>1,2</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201602003]]></guid><cfi:id>234</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Effective thermal analysis of platelet heat-pipe-cooled leading edge of vehicle]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201602004]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[A new structure, the platelet heatpipecooled leading edge, was proposed for hypersonic vehicle thermal protection. In order to avoid the challenge of modeling two-phase conjugate heat and mass transfer, an approach of modeling the vapor core as a solid thermal conductor with high conductivity was adopted and the effective vapor thermal conductivity was deduced mathematically. Its effectiveness was validated by comparing the wall temperature against experimental date for a conventional heat pipe. The research result indicates that the nickel based alloy IN718, with sodium as the working fluid, is a feasible combination form Mach 7 with a 15 mm leading edge radius.]]></description>
<pubDate>2016/5/6 16:32:20</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LIU Hongpeng<sup>1,2</sup> and LIU Weiqiang<sup>1,2</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LIU Hongpeng<sup>1,2</sup> and LIU Weiqiang<sup>1,2</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201602004]]></guid><cfi:id>233</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Feasibility analysis of solenoid-based magnetohydrodynamic heat shield system for hypersonic vehicles]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201602005]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In order to analyze the feasibility of MHD (magnetohydrodynamic) heat shield system for the nose cone of hypersonic vehicles, a normal columned solenoid-based MHD thermal protection system model was built. By using the low magneto-Reynolds MHD model, a set of numerical simulations for hypersonic nose cone with external magnetic field were performed; the feasible range of magnetic induction intensity of normal solenoid-based MHD heat shield system was obtained; the requirements of the solenoid's geometric parameters were drawn to meet the limit of coil current density. Results show that, considering the saturation effect and the current density limit existing in the process of MHD thermal protection, the system works better when the stagnation magnetic induction intensity B<sub>0</sub> is in the range of 0.05～0.20 T. When B<sub>0</sub> is equal to 0.20 T, the stagnation heat flux density and total wall heat flux is reduced by 31.3% and 56.6% respectively, indicating the effectiveness of thermal protection. However, the required coil mass is so heavy that its structure must be optimized to be actually utilized.]]></description>
<pubDate>2016/5/6 16:32:20</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LI Kai and LIU Weiqiang]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LI Kai and LIU Weiqiang</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201602005]]></guid><cfi:id>232</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Simulation analysis of outer edge boundary parameters for hypersonic-glide vehicle]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201602006]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Method of inviscid flow field simulation of the outer edge boundary layer for hypersonic vehicle was created, which was faster than the numerical method and more accurate than the engineering method. And the curve of specific heat and the specific heat ratio changed with temperature were matched, which deduced the law of air attribute on different temperatures. Based on the law, the model of parameters of the outer edge boundary layer for hypersonic vehicle was built, and the comparisons of the results of the proposed method and the engineering method as well as the viscid method of blunt double-cone model were analyzed. Result shows that at the 0° angle of attack, compared with the viscid method, the maximum differences of the pressures between engineering method and viscid method are about 1.19% and 2.39% respectively, while at the 10°angle of attack, they are about 5% and 50% respectively. And the proposed inviscid numerical method obtained higher accuracy is superior to the engineering method, which lays the foundation for the thermal environment calculation of hypersonic-glide vehicle.]]></description>
<pubDate>2016/5/6 16:32:20</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[MENG Zhuxuan<sup>1</sup>, HU Fan<sup>1,2</sup>, PENG Ke<sup>1</sup> and ZHANG Weihua<sup>1,2</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>MENG Zhuxuan<sup>1</sup>, HU Fan<sup>1,2</sup>, PENG Ke<sup>1</sup> and ZHANG Weihua<sup>1,2</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201602006]]></guid><cfi:id>231</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Experimental observation of non-reaction flow field based on cavity supersonic combustor on condition of side wall shock wave]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201602007]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Side wall shock wave was introduced in supersonic combustor based on cavity. In order to study the internal flow characteristics of the combustor, nanoparticle planer laser scattering and particle image velocimetry technologies were employed to observe internal flow field of combustor model made by glass. Gray images and average velocity distributions of non-reaction flow field in side view and top view were caught by experimental facilities. Observation results reveal that: speed and density of fluid inside cavity are low in the region far away from the side wall; mass and momentum exchange is enhanced in the region near the side wall on condition of side wall shock wave with high speed and density; boundary layer of combustor bottom wall becomes nonuniform due to side wall shock waves, and large scale of low speed region generates at the rear of cavity with obvious three-dimensional characteristics.]]></description>
<pubDate>2016/5/6 16:32:20</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[ZHAO Yanhui and LIANG Jianhan]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>ZHAO Yanhui and LIANG Jianhan</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201602007]]></guid><cfi:id>230</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Parametric of an integrated thermoelectric generation thermal management system for hypersonic vehicle]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201602008]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[An integrated thermoelectric generation thermal management system for a regenerative cooling scramjet was proposed. Thermoelectric power generators were integrated in the scramjet structure. The integrated thermoelectric generation thermal management system reduces the fuel flux for cooling, through converting part of the energy by heat conduction on the scramjet structure to electric power. The heat that must be taken away by fuel is decreased and the fuel cooling capacity is indirectly increased. At the same time, high temperature and high pressure fuel also has the capacity for doing work. It flows through a turbine and get additional power output for the use of hypersonic vehicle. A parametric study of the integrated  thermoelectric generation thermal management system for scramjet was performed. It is known through performance analysis that the integrated thermoelectric generation thermal management system has excellent potential performance over the conventional regenerative cooling. The fuel flux is reduced while the integrated thermoelectric generation thermal management system gives power output.]]></description>
<pubDate>2016/5/6 16:32:20</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LI Xinchun<sup>1,2</sup> and WANG Zhongwei<sup>1,2</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LI Xinchun<sup>1,2</sup> and WANG Zhongwei<sup>1,2</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201602008]]></guid><cfi:id>229</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Effect of transverse forcing on passive scalar mixing in supersonic mixing layer]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201602009]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Numerical studies on a spatially developing supersonic mixing layer were performed by means of large-eddy simulation. Focusing on the effect of transverse forcing on the passive scalar mixing characteristic of mixing layer. The results for the baseline case without external forcing are in agreement with the analytical evidence. Afterwards, the effect of transverse forcing on the scalar structure, scalar thickness and volumetric entrainment ratio of mixing layer were analyzed. Results indicate that the frequency and amplitude of transverse forcing alter the growth rate and entrainment ratio of the passive scalar mixing significantly. High-frequency forcing magnifies the scalar thickness and volumetric entrainment ratio in the near field of mixing layer. However,  the growth rate in the far field is increased by the low-frequency forcing. The entrainment ratio is, to be a large extent, dominated by the large-scale eddy entrainment process. The multiple-frequency forcing seems to validly enhance the scalar mixing in supersonic mixing layer.]]></description>
<pubDate>2016/5/6 16:32:20</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[FENG Junhong<sup>1,2</sup> and SHEN Chibing<sup>1,2</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>FENG Junhong<sup>1,2</sup> and SHEN Chibing<sup>1,2</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201602009]]></guid><cfi:id>228</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[High-order finite volume schemes in three-dimensional curvilinear coordinate system]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201602010]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In order to develop a high-order finite volume scheme, which can perform with high fidelity in smooth regions, capture the discontinuities without oscillation, and overcome the difficulty in choosing stencils, a high-order finite volume scheme on structure meshes was developed on the basis of dimension-by-dimension reconstruction method. The scheme was also extended to the three-dimensional curvilinear coordinate system, which was suitable for the computation under relatively complex configurations. In order to validate the numerical scheme, some test cases were used. In the cases of the isentropic vortex and two-dimensional channel flow, it was found that the designed order of accuracy could be achieved. In the double Mach problem, it was proved that the scheme could well capture the discontinuities. The test cases show that the scheme has high numerical accuracy and robust capturing ability on curvilinear meshes and high efficiency in the simulations of the computational fluids dynamics.]]></description>
<pubDate>2016/5/6 16:32:20</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[XU Dan<sup>1</sup>, WANG Dongfang<sup>1</sup>, CHEN Yaming<sup>2</sup> and DENG Xiaogang<sup>1</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>XU Dan<sup>1</sup>, WANG Dongfang<sup>1</sup>, CHEN Yaming<sup>2</sup> and DENG Xiaogang<sup>1</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201602010]]></guid><cfi:id>227</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Processing properties of heat resistant epoxy resin systems for injection repairing]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201602026]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The curing properties and chemorheological behaviors of the three heat resistant glyceramine epoxy resin systems for the injection repairing were measured by the isothermal differential scanning calorimetry and the rotational rheometer to investigate the curing cycle and the chemorheological characteristics of the resin systems. The MF-4101/ZH110/DMP-30 resin systems were proved to be the most suitable formulation for injection repairing by comparing the curing conditions and viscosities of the three resin systems. The Daul Arrhenius model and the highorder exponential fitting model were established to analyze the isothermal viscositytime curves of the resin system. Results show that the accuracy and the applicability of the high-order exponential fitting model for viscosity predicting are superior to the Daul Arrhenius model. The predicted results of the high-order exponential fitting model are in  good agreement with the experimental data. This phenomenological formula based on the above model can be used to predict the processing windows of injection repairing resin systems. ]]></description>
<pubDate>2016/5/6 16:32:22</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[WU Hai, XIAO Jiayu, XING Suli, WEN Siwei and YANG Jinshui]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>WU Hai, XIAO Jiayu, XING Suli, WEN Siwei and YANG Jinshui</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201602026]]></guid><cfi:id>226</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Numerical research on forced convective heat transfer of stratospheric airships]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201602029]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[During the floating flight, the complex radiation-convection environment remarkably affects the flight performance and security of the stratospheric airship. The forced convection around the stratospheric airship plays an important role in the thermal behavior of the airship. Based on the hypothesis of pure heat conduction inside the airship, a three dimensional CFD model of stratospheric airships was developed and the thermal characteristics of the forced convective heat transfer of the airship were investigated. The distributions of the temperature of skins of the airship and the average temperature of the inner gas were calculated with the variation of the angle of the sun, the wind velocity and the angle of attack. Simulation results can be referenced for the accurate prediction of the thermal behavior of stratospheric airships.]]></description>
<pubDate>2016/5/6 16:32:23</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[WU Jiangtao, MA Zhenyu, HOU Zhongxi and LIU Zhaowei]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>WU Jiangtao, MA Zhenyu, HOU Zhongxi and LIU Zhaowei</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201602029]]></guid><cfi:id>225</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Sequential approximate optimization method and its application in rapid design of rocket shape]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201601021]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Sequential approximate optimization method has shortcomings in several respects, such as surrogate model establishing and infill strategy at present. Basing on local density of sampling points, the influence volume concept which is inversely proportional to local density was introduced and then the optimal kernel width of radial basis function was obtained by means of total influence volume optimization, thus, the function approximation needs in sequential approximate optimization process under the conditions of different scales and heterogeneous samples were satisfied. Potential feasible region infill strategy was proposed and potential optimal strategy was applied together, both exploration and exploitation capacity of the algorithm were satisfied. Three-step convergence criterion was set up. The algorithm flow process of sequential approximate optimization was constructed. For Golinski reducer optimization problem,the global optimal solution was solved after calculating original model 42 times, which embodied the good global optimization capacity and searching efficiency of the algorithm. Shape optimization mathematical model was established for TH-II rocket, global optimal shape was gained after 165 times of original model calling using the proposed method. The design efficiency was increased greatly and TH-II rocket aerodynamic shape was proved reliable by flight testing.]]></description>
<pubDate>2016/3/7 9:21:22</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[PENG Ke, HU Fan, ZHANG Weihua and WU Zeping]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>PENG Ke, HU Fan, ZHANG Weihua and WU Zeping</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201601021]]></guid><cfi:id>224</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Global optimization of solar sail gravity assist and solar photonic assist trajectory for interstellar mission]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201601022]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[With the goal of solar sail mission to near interstellar space (200AU) in 20 years, a global optimization problem of solar sail gravity assist and solar photonic assist trajectory for interstellar mission was studied. A mathematical model for solar sail time-optimal trajectory was established. By taking the constrains of solar sail gravity assist and solar photonic assist into the object function, the four-point boundary value problem of orbit optimization can be converted to multi-variable optimization problem of no constraint. With choosing appropriate constrain proportions, the problem was solved by using genetic algorithm and sequential quadratic programming method. Optimization result shows that plenty of time can be saved by adding Jupiter gravity assist, though solar sail gains a large velocity with solar photonic assist. The proposed global optimization algorithm will provide a reference for the preliminary design of solar system escape orbit.]]></description>
<pubDate>2016/3/7 9:21:22</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[QIAN Hang<sup>1,3</sup>, ZHENG Jianhua<sup>1</sup>, LI Mingtao<sup>1</sup>, LI Hui<sup>2</sup>, GAO Dong<sup>1</sup> and YU Xizheng<sup>1</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>QIAN Hang<sup>1,3</sup>, ZHENG Jianhua<sup>1</sup>, LI Mingtao<sup>1</sup>, LI Hui<sup>2</sup>, GAO Dong<sup>1</sup> and YU Xizheng<sup>1</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201601022]]></guid><cfi:id>223</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Design and analysis of footprint optimization method for multiple-pulse missile]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201601023]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In order to formulate tactical indicators and mission plan，the footprint for multiple-pulse missile was investigated. The footprint optimization problem can be transformed into an optimal control problem by introducing the cost function which is formulated as a weighted combination of down-range and cross-range. A multiple constraints and phases trajectory optimization model of double optimization design variables that are composed by the angle of attack and slip angle was established，and using the  hp-adaptive pseudo-spectral method to solve it. Moreover, the effects of multiple-pulse motor parameters and terminal constraints on the footprint were emphatically analyzed. Simulation results show the efficiency of the proposed method in solving the footprint optimization design problem with multiple constraints and phases. The smaller interval time of multiple-pulse missile motor，the greater of thrust radio and the smaller mass radio of the pulse motor are corresponded to a bigger footprint. Compared with the terminal velocity, the impact angle affects the footprint to a lesser degree．]]></description>
<pubDate>2016/3/7 0:00:00</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[MING Chao<sup>1</sup>, SUN Ruisheng<sup>1</sup>, LIANG Zhuo<sup>2</sup> and BAI Hongyang<sup>1</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>MING Chao<sup>1</sup>, SUN Ruisheng<sup>1</sup>, LIANG Zhuo<sup>2</sup> and BAI Hongyang<sup>1</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201601023]]></guid><cfi:id>222</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Form optimization design of space net using small elastic modulus method]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201706001]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Form design of net can help to improve the opening and capturing quality of the space net system. The form optimization design problem of space net was studied based on small elastic modulus method. Internal force distributed in the net was selected as the optimization objective. The maximum stress state was chosen as the research condition and the rope was given minimum modulus elasticity. The iteration analysis was carried out using the results of deformation as the initial condition. Optimization results show that the internal force distribution of the rope net tends to be more uniform with the increase of the iteration steps. Without changing the premise of net topology structure, the established optimization design and method for the space net configuration optimization design and provides a means of reference.]]></description>
<pubDate>2018/1/16 17:02:00</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[GAO Qingyu, ZHANG Qingbin, TANG Qiangang and FENG Zhiwei]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>GAO Qingyu, ZHANG Qingbin, TANG Qiangang and FENG Zhiwei</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201706001]]></guid><cfi:id>221</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Two-stage control guidance of missile impact angle and flight time]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201706002]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The impact angle and the flight time were needed to be controlled simultaneously for a saturation attack. A two-stage guidance strategy with impact angle and flight time was proposed for impact angle and flight time control. In the first stage, the impact time high-precision control guidance law was derived by using a switching surface in pitch channel. The traditional proportional guidance law was used in yaw channel. Then in the second stage, the trajectory shaping optimal guidance with gravity compensation was used for impact angle control, which was an extension of explicit guidance in that gravity compensation was incorporated. The effectiveness of the impact angle and impact time two-stage guidance was validated by simulation. Simulation results show that the proposed two-stage control guidance with impact angle and flight time can achieve the simultaneous control of the impact angle and flight time.]]></description>
<pubDate>2018/1/16 17:02:00</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LI Xinsan<sup>1,2</sup>, WANG Lixin<sup>1</sup>, FAN Xiaohu<sup>2</sup>, DING Bangping<sup>2</sup>, XUE Liang<sup>1</sup> and WANG Mingjian<sup>2</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LI Xinsan<sup>1,2</sup>, WANG Lixin<sup>1</sup>, FAN Xiaohu<sup>2</sup>, DING Bangping<sup>2</sup>, XUE Liang<sup>1</sup> and WANG Mingjian<sup>2</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201706002]]></guid><cfi:id>220</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Effect of time span on GPS time series noise model and velocity estimation]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201706003]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The time series of 72 international GPS service core stations were selected to make perform analysis on GPS noise model and uncertainties of the velocity. An improved Akaike information criteria and a Bayesian information criteria model were developed to evaluate different combinations of noise model, so as to establish the best noise model of GPS time series and gain the aureate velocity parameters. Results show that the noise model of GPS time series cannot be described as simple noise, it tends to showing diversity, and can be best described by power-law, generalized Gauss Markov, flicker noise plus white noise model, and its three components exhibit different noise characteristics. With the time span increases, the optimal noise model of time series, GPS station velocity and its uncertainty tends to be convergent and steady. Besides, the proportion of random walk noise is proved to increase as time span increases. The final results show that the time span of more than 10 years is an ideal noise model estimation scale.]]></description>
<pubDate>2018/1/16 17:02:00</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[HE Xiaoxing<sup>1,2</sup>, HUA Xianghong<sup>1</sup>, LU Tieding<sup>3</sup>, YU Kegen<sup>1</sup> and XUAN Wei<sup>1</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>HE Xiaoxing<sup>1,2</sup>, HUA Xianghong<sup>1</sup>, LU Tieding<sup>3</sup>, YU Kegen<sup>1</sup> and XUAN Wei<sup>1</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201706003]]></guid><cfi:id>219</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Space debris impact risk assessment model and its application]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201706004]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[A space debris impact risk assessment model was developed on the basis of the existing space debris environment model. The framework of the model consists of space debris environment module, spacecraft model module, geometry shading module and impact probability module. The impact risk by space debris for three generic spacecraft geometries were offered by IADC in order to validate different models. The result was proved to be effective by comparing with other models. The space debris impact risk for the spacecraft of cube was assessed and analyzed using the developed risk assessment model, and the effect of orbital altitude, inclination and attitude parameters to the space debris impact risk was presented.]]></description>
<pubDate>2018/1/16 17:02:00</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LIANG Yangang and QIN Zheng]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LIANG Yangang and QIN Zheng</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201706004]]></guid><cfi:id>218</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Multi-objective evolutionary search algorithm for geomagnetic bio-inspired  navigation]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201706015]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Aiming to solve the search problem of geomagnetic multi-component and multiobjective, the multi-objective evolutionary search algorithm based on the magneto-taxis sensitivity was proposed for the autonomous underwater vehicles. Combined with the structure of the evolutionary algorithm, this method utilized the restrictive correlation between the geomagnetic components and the navigation path, and the magneto-taxis sensitivity was expressed as a posteriori assessment criteria to establish the navigation model. The geomagnetic multi-component converged to desired value along with the motion of the vehicle at the same time and place, thus realized the navigation goal. Compared with the hex-path searching algorithm, the effectiveness and advantages of the proposed algorithm were validated by the simulation experiments.]]></description>
<pubDate>2018/1/16 17:02:01</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LI Hong, LIU Mingyong and LIU Kun]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LI Hong, LIU Mingyong and LIU Kun</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201706015]]></guid><cfi:id>217</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Varying resolution digital elevation model with surface curvature analysis]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201706025]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Digital elevation model with regular grids simplifies the modeling and analyzing processes. However, it fails to adapt to different terrain shapes and it is hard to obtain high surface accuracy and small dataset in the meantime, which limits its application in areas such as vehicle dynamic simulation. To solve this problem, a modeling method with varying data resolution was proposed. The node density varied according to the local surface curvature so that it ensures high data resolution around sharp changing areas and low data resolution around relatively flat area. Then Delaunay gridding method together with cubic interpolation was applied to obtain a digital elevation model with high surface accuracy and small data size using the resulting irregular node set. The proposed method was testified with a complex terrain surface used in rover simulation, and compared with the traditional regular grid model, which verified its advantages in achieving the two major objectives. ]]></description>
<pubDate>2018/1/16 17:02:00</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[XIE Yangmin<sup>1</sup>, GUO Yukun<sup>1,2</sup>, ZOU Huaiwu<sup>2</sup> and SHI Hang<sup>2</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>XIE Yangmin<sup>1</sup>, GUO Yukun<sup>1,2</sup>, ZOU Huaiwu<sup>2</sup> and SHI Hang<sup>2</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201706025]]></guid><cfi:id>216</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Modified tracking differentiator design for missile in hardware-in-loop simulation system]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201705012]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In order to inhibit the influence of the output signals of three-axis simulator exhibited the phase delays and noise on the performance of missile’s hardware-in-loop simulation system, a modified tracking differentiator which was used to filter and phase advance was analyzed and designed. Based on the principle of traditional tracking differentiator, the basic structure of tracking the output signals of threeaxis simulator was designed. Due to the differential signal obtained from the tracking differentiator trembles existed noise, the vibration phenomenon of the output signals was analyzed. On this basis, a design method that the differential signal cascaded another tracking differentiator was proposed to filter the signal pollution and output signals noise. Finally, as the examples of one missile’s hardware-in-loop simulation system which were the output signals of three-axis simulator exhibited the phase delays and noise, the performance of the system was verified by comparing with the lead correction method. Simulation results show that the attitude angular velocity can be extracted by the modified phase advancer efficiently, and the modified phase advancer possesses excellent filter and phase advanced performance, which prove the correctness and validity of the modified phase advancer in the hardware-in-loop simulation system for missile.]]></description>
<pubDate>2017/11/7 15:44:02</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[MING Chao<sup>1</sup>, SUN Ruisheng<sup>1</sup>, BAI Hongyang<sup>1</sup> and ZHU Gang<sup>2</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>MING Chao<sup>1</sup>, SUN Ruisheng<sup>1</sup>, BAI Hongyang<sup>1</sup> and ZHU Gang<sup>2</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201705012]]></guid><cfi:id>215</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Creep behavior and life predication for anti-detaching spring]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201705013]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[According to the loading mode and failure mechanism of a certain anti-detaching spring, a testing device for creep of anti-detaching spring was designed and manufactured. The creep accelerated aging test was done, and the effect of the temperature and loading on the creep behavior of antidetaching spring was investigated with image measuring technology. Furthermore, the creep kinetic equation of anti-detaching spring subjected to loading and temperature based on Arrhenius equation was derived to predict the service life of the anti-detaching spring. The results show that the displacement of the spring due to creep is a monotonic non-decreasing function of time. Increasing the temperature or initial preload will result in accelerating its creep displacement. The method and conclusion may be helpful in creep anti-detaching spring design and life prediction.]]></description>
<pubDate>2017/11/7 15:44:03</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[KONG Fanjie<sup>1</sup>, CUI Huiru<sup>2</sup>, LIU Xiayang<sup>1</sup>, YAN Lu<sup>1</sup> and JI Baofeng<sup>1</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>KONG Fanjie<sup>1</sup>, CUI Huiru<sup>2</sup>, LIU Xiayang<sup>1</sup>, YAN Lu<sup>1</sup> and JI Baofeng<sup>1</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201705013]]></guid><cfi:id>214</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Extended multiple model adaptive method for fault detection and diagnosis of launch vehicle′s servo mechanism]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201705014]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Aiming at the servo mechanism fault of launch vehicle, a FDD (fault detection and diagnosis）based on extended multiple model adaptive estimation was proposed. Attitude dynamic model of launch vehicle considering servo mechanism fault was established; the fault angle was used as the state variable to obtain the augmented state space model; the nonlinear estimation of state vectors and fault parameters was carried out by using the extended Kalman filter, and based on the sensor measurement data, the occurrence probability of faults was calculated by the hypothesis testing algorithm; the fault detection and diagnosis procedure based on the extended multiple model adaptive estimation was presented. Simulation results shows that, not only the health monitoring of the servo mechanism can be carried out by the algorithm without fault, but also under single servo mechanism fault, the core servo mechanism whose fault appeared can be timely and exactly detected through the algorithm, and the angle of nozzle under servo mechanism fault can be estimated accurately.]]></description>
<pubDate>2017/11/7 15:44:03</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[CHENG Tangming<sup>1,2</sup>, LI Jiawen<sup>1</sup>, CHEN Yu<sup>2</sup> and TANG Guojin<sup>1</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>CHENG Tangming<sup>1,2</sup>, LI Jiawen<sup>1</sup>, CHEN Yu<sup>2</sup> and TANG Guojin<sup>1</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201705014]]></guid><cfi:id>213</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Application of multisensor information fusion in UAV relative navigation method]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201705015]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In order to improve the operational effectiveness and operational indicators of the UAV (unmanned aerial vehicle), and to enhance the accuracy and reliability of the UAV relative navigation system, a novel relative navigation method was proposed. Under the background of relative navigation system, the cubature information filter based on the cubature Kalman filter and information filter was studied. Moreover, an INS/GPS/VisNav relative navigation filter was designed by making use of the multi-sensor information fusion theory and distributed information fusion structure to fuse the information from INS, VisNav and GPS, and then the relative position, velocity and attitude were obtained. By making use of this algorithm, the accuracy, reliability and stability of the reliability navigation system were all improved. In addition, the accuracy decrease and numerical instability which often occur to traditional filter were avoided by cubature information filter. Mathematical simulation results indicate that the method can improve the accuracy and reliability of the UAV relative navigation system, and the proposed algorithm is verified.]]></description>
<pubDate>2017/11/7 15:44:03</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[JIN Hongxin<sup>1,2</sup>, YANG Tao<sup>1</sup>, WANG Xiaogang<sup>3</sup>, ZHOU Guofeng<sup>2</sup> and YAO Wang<sup>2</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>JIN Hongxin<sup>1,2</sup>, YANG Tao<sup>1</sup>, WANG Xiaogang<sup>3</sup>, ZHOU Guofeng<sup>2</sup> and YAO Wang<sup>2</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201705015]]></guid><cfi:id>212</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Analysis on effects of vertical deflection for trajectory impact accuracy]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201704001]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In view of the effects of the vertical deflection on trajectory impact accuracy, the influence mechanisms of the vertical deflection on the launching coordinate system, the initial parameter, the force during the flight, the control criteria of the program angle, and the trajectory parameter under the geocentric coordinate system were analyzed respectively by combining with the particle dynamics model of the ballistic vehicle. Then, the mathematical models of the effects of the vertical deflection were established. Furthermore, based on the given computing method of trajectory impact deflection and taking a flight trajectory as example, the impact errors under different geodetic latitude of launch point and different launch azimuth angle were presented quantitatively. The research is of great reference value  in the aspect of the improvement of the impact accuracy for the ballistic vehicle.]]></description>
<pubDate>2017/9/12 10:09:49</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[CHANG Xiaohua, JIANG Lujia, YANG Rui, ZHANG Jie and FENG Hai]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>CHANG Xiaohua, JIANG Lujia, YANG Rui, ZHANG Jie and FENG Hai</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201704001]]></guid><cfi:id>211</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Control for 6-DOF relative motion of spacecraft with input saturation constraint using dual quaternion]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201704002]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The dual quaternion was used to investigate the 6-DOF (six degree-of-freedom) relative motion of spacecraft, and an integrated controller of attitude and orbit with input saturation constraint was designed. Firstly, the dual number and dual quaternion  followed by the derivation of 6-DOF relative motion of attitude and orbit coupled model were introduced. Then, an explicitly bounded controller was proposed by using the property that the absolute value of hyperbolic tangent function was less than 1. Two coupled adaptive regulators were respectively designed to adjust the outputs of the controller dynamically. Thirdly, it is proved by a rigorous theoretical analysis that the closedloop system is globally and asymptotically stable. Finally, numerical simulation experiment is implemented to demonstrate the validity and effectiveness of the proposed controller. Experimental results show that both the obtained control torque and control force satisfy the given constraints, the 6-DOF relative motion of spacecraft can be controlled accurately and the method is robust to parameter uncertainties and external disturbance. Compared with other methods, the proposed method has the following advantages: the convergence rate is faster,  the max magnitude of output control torque and control force are both smaller, and the consumed energy is less.]]></description>
<pubDate>2017/9/12 10:09:49</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[CHEN Chen<sup>1</sup>, WU Jinjie<sup>2</sup>, WANG Xiaoyu<sup>3</sup>, LI Dongxu<sup>4</sup> and ZHENG Wei<sup>5</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>CHEN Chen<sup>1</sup>, WU Jinjie<sup>2</sup>, WANG Xiaoyu<sup>3</sup>, LI Dongxu<sup>4</sup> and ZHENG Wei<sup>5</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201704002]]></guid><cfi:id>210</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Force balance in dynamic soaring of aerial vehicle]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201704003]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[To clarify the physical essential, a perspective of force balance to dynamic soaring was put forward. Equilibrium equations were derived according to physical laws. The solution of the equations solved mathematically formed a curve. Simulations of the curve  were made in the cases of an albatross and an unmanned air vehicle in different wind gradients for instances. The results of analysis and simulation indicate that the curve is the velocity set that satisfies the equilibrium equations; the curve consists of a climbing branch and a diving one; the climbing branch exists only if the gradient is sufficiently large, and it is critical to dynamic soaring.]]></description>
<pubDate>2017/9/12 10:09:49</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[SHAN Shangqiu, HOU Zhongxi, WANG Peng and GUO Zheng]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>SHAN Shangqiu, HOU Zhongxi, WANG Peng and GUO Zheng</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201704003]]></guid><cfi:id>209</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[KD tree method for efficient wall distance computation of mesh]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201704004]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In some fields of computational fluid dynamics, the nearest distance from a certain point in the flow field to the wall surface is usually required. In order to improve the precision as well as the efficiency of the computation result, the KD tree method was applied to the wall distance computation of unstructured mesh, and then the wall distances of several three dimensional configurations were computed. Results show that the method computing wall distances based on KD tree can achieve the capability of great robustness,  high efficiency and precision, and is suitable for complex configuration. Besides, the method has good universality so that it can be applied to many other types of mesh.]]></description>
<pubDate>2017/9/12 10:09:49</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[GUO Zhongzhou<sup>1</sup>, HE Zhiqiang<sup>1</sup>, XIA Chenchao<sup>2</sup> and CHEN Weifang<sup>1</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>GUO Zhongzhou<sup>1</sup>, HE Zhiqiang<sup>1</sup>, XIA Chenchao<sup>2</sup> and CHEN Weifang<sup>1</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201704004]]></guid><cfi:id>208</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Mathematical models of lunar orbit shadow and optimization of lunar orbits]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201704005]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Mathematical models of lunar and Earth shadow were established for lunar orbits. Also, the criterion was proposed to decide whether the satellite was in the shadow area. Golden section search optimization was used to search out the boundary values of the shadow area. In combination with specific cases, the optimal targeting lunar orbit was given  by the genetic algorithm which was embedded in tabu search. The mathematical models of lunar orbit shadow given out in this article are simple enough to be used in onboard computer. Meanwhile, they can meet the engineering accuracy requirements. The embedded genetic algorithm has advantage of fast convergence without trapping in local optimum.]]></description>
<pubDate>2017/9/12 10:09:49</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[QIU Shi, CAO Xibin and ZHANG Jinxiu]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>QIU Shi, CAO Xibin and ZHANG Jinxiu</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201704005]]></guid><cfi:id>207</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Closedloop covariance analysis for orbital rendezvous using square root unscented Kalman filter based on angles-only navigation]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201704006]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[A closed-loop linear covariance analysis method was proposed for orbital rendezvous using AON (angles-only navigation). The SRUKF (square root unscented Kalman filter) based on AON algorithm was constructed and the observation sensitivity matrix was further calculated. The multi-impulsive Hill guidance law was employed to derive the closed-loop linear covariance analysis model. The results of the numerical simulation indicate that the closedloop linear covariance analysis result fits the 1000 times Monte Carlo shooting well. The covariance analysis method is applicable to the traditional EKF (extended Kalman filter) based on the AON method, but has an estimation bias along downrange, which is equivalent to the variance of trajectory dispersion. The major axis and minor axis of error ellipse achieved with EKF based on covariance respectively are about 24.68% and 20.56% longer than the results from SRUKF based error ellipse. Besides, SRUKF and EKF have the same order computational burden for the state estimation, but the SRUKF is about 10% faster than the EKF due to using two powerful linear algebra techniques, QR decomposition and Cholesky factor updating.]]></description>
<pubDate>2017/9/12 10:09:49</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[YOU Yu<sup>1,2</sup>, WANG Hua<sup>1</sup>, Christophe Paccolat<sup>2</sup> and LI Jiuren<sup>3</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>YOU Yu<sup>1,2</sup>, WANG Hua<sup>1</sup>, Christophe Paccolat<sup>2</sup> and LI Jiuren<sup>3</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201704006]]></guid><cfi:id>206</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Indirect detection method of atmospheric density based on hypersonic reentry sphere]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201704007]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[A near space atmospheric density detection method based on hypersonic reentry sphere was proposed with the aim of overcoming the shortages of current detection methods, such as the low accuracy, the high cost and the weak time-space conformity. The measurement error was analyzed according to the kinematic equation of reentry sphere. The results show that the atmospheric density below the height of 90 km can be detected with the accuracy level below 6%. The antenna placement scheme was determined by analyzing the 6-DOF (degree of freedom) motion model of the sphere with eccentric balancing weight and combining with the numerical simulation of aerodynamic heat. Numerical calculation of heat conduction along ballistic trajectory for the eccentric sphere with double radome was achieved and the thermal protection scheme was performed eventually to demonstrate the feasibility of this detection scheme. The proposed detection method of atmospheric density can provide a meaningful reference to the construction of highaccuracy nearspace atmospheric density.]]></description>
<pubDate>2017/9/12 10:09:49</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LI Haoge, ZHU Hengwei, WU Changju and CHEN Weifang]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LI Haoge, ZHU Hengwei, WU Changju and CHEN Weifang</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201704007]]></guid><cfi:id>205</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Guidance law with maneuvering efficiency constraint considering missile dynamic characteristics]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201704008]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Due to the guidance law with terminal intercept angle and payload constraints which can cause big engorge loss, a guidance law considering maneuvering efficiency constraint was proposed. A closed-loop sub-optimum guidance law with time-varying control weight coefficient considering first-order missile dynamic characteristics was elicited according to the optimal quadratic theory; The drag coefficient was introduced into the time-varying control weight coefficient, and the constraint boundary of maneuvering efficiency through iterations was obtained; the time-varying weight coefficient was changed into function of time-to-go and delay time, and the trajectories with guidance law considering maneuvering efficiency was emulated. Results indicate that, for constant velocity and maneuvering target, the new guidance law and the guidance law with payload constraint can meet the requirement of trajectory shaping when compared with the guidance law with intercept angle, and the acceleration command of guidance law with constraint considering maneuvering is more reasonable. And the new guidance law can reduce the velocity loss and avoid the payload saturation at the same time, and enhance the guidance accuracy and damage effect. Moreover, it is not necessary to balance solutions of time-varying weight coefficient, so the iteration speed will be improved when accuracy is guaranteed.]]></description>
<pubDate>2017/9/12 10:09:49</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[WANG Chaolun, XUE Lin and YAN Xiaoyong]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>WANG Chaolun, XUE Lin and YAN Xiaoyong</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201704008]]></guid><cfi:id>204</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Efficient method for firing data calculation of boost-glide missile in mobile condition]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201704009]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Considering the urgent need of rapid trajectory generation of boost-glide missile in mobile condition, seven key parameters of control variables were selected as the firing data, and the corresponding iterative calculation algorithms were proposed. The full-range trajectory was divided into the boost phase, initial phase, glide phase and dive attack phase, all these flight phases were described in a unified dynamics model. Firing data in different phases were calculated rapidly one by one, and multiple constraints were satisfied strictly, with the help of the parameterized iterative algorithm. Furthermore, a partly recalculation mode which uses the firing data of the center trajectory in the boost phase and recalculates the others was proposed on the basis of the full mode. The simulation results indicate that this method can achieve a great performance in the quick attack to a ground stationary target in mobile condition.]]></description>
<pubDate>2017/9/12 10:09:49</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[HE Ruizhi<sup>1</sup>, LIU Luhua<sup>1</sup>, TANG Guojian<sup>1</sup> and BAO Weimin<sup>1,2</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>HE Ruizhi<sup>1</sup>, LIU Luhua<sup>1</sup>, TANG Guojian<sup>1</sup> and BAO Weimin<sup>1,2</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201704009]]></guid><cfi:id>203</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Aerodynamic configuration design and analysis of near-space high supersonic unmanned aerial vehicle]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201704010]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Aerodynamic configurations in the conceptual design of a near-space HSUAV (high supersonic unmanned aerial vehicle) were investigated. To accelerate the aerodynamic configuration design process, a set of tools for the aerodynamic configuration design and analysis, including the parametric geometry modeling code, the grid generation script, the flow field analysis software and the aerodynamic result analysis code, were developed. Following the request for proposal of the HSUAV, an aerodynamic configuration for the HSUAV, in which the wing was integrated into fuselage, was proposed. The wing used a double-wedge airfoil, and the empennage was in V tail. In order to meet the requirement of the air mass flow captured by the inlet, the straight leading edge of the HSUAV was modified into the arched leading edge. Numerical simulation method was employed to evaluate the aerodynamic characteristics of the HSUAV configurations with different wing aspect ratios and dihedrals. Based on the evaluations, the most suitable wing aspect ratio and dihedral were selected, and the final aerodynamic configuration for the HSUAV was obtained. The viability of the final aerodynamic configuration of the HSUAV was verified by the detailed flow field analysis.]]></description>
<pubDate>2017/9/12 0:00:00</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[YOU Lianxing<sup>1,2</sup>, YU Xiongqing<sup>1</sup> and WANG Yu<sup>1</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>YOU Lianxing<sup>1,2</sup>, YU Xiongqing<sup>1</sup> and WANG Yu<sup>1</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201704010]]></guid><cfi:id>202</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[SAR platform location method based on scene matching and inertial navigation system information]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201704016]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Aided by elevation information provided by height sensor, SAR (synthetic aperture radar) platform geo-location was realized by combining the high-precision image matching technology and the INS (inertial navigation system) drift correction method. According to the fact that the platform is on the centerline of SAR image at the middle imaging time, some points on the centerline of a single image were equably selected to conduct the high precision matching with the optical reference image. The projection position of SAR platform on the horizontal plane was calculated and the spatial position was positioned by making use of the elevation information. By use of the position results of sequence images, the drifting parameters of INS were estimated and then the outputting position data were corrected to achieve the high-accuracy platform geo-location. The impacts of different errors on location precision were analyzed and the precision estimation formulas were derived. Both simulation and real data test results show high precision and practical value for engineering of the proposed method.]]></description>
<pubDate>2017/9/12 10:09:50</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[CHEN Shengyi<sup>1,2</sup>, LIU Xiaochun<sup>1,2</sup>, LEI Zhihui<sup>1,2</sup>, YU Qifeng<sup>1,2</sup> and CUI Wen<sup>3</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>CHEN Shengyi<sup>1,2</sup>, LIU Xiaochun<sup>1,2</sup>, LEI Zhihui<sup>1,2</sup>, YU Qifeng<sup>1,2</sup> and CUI Wen<sup>3</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201704016]]></guid><cfi:id>201</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Bank-to-turn coupling control strategy for hypersonic vehicle]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201704019]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[A coupling control strategy was proposed for the BTT (banktoturn) flight phase of hypersonic vehicle, according to the strong coupling among the channels of pitch, yaw, and rolling. Based on the nonlinear generable predictive control method, a hierarchy-structured predictive controller was designed and analyzed for rotation motion dynamics of a generic hypersonic vehicle, which has the characteristics of fast variability,  high nonlinearity, and uncertain parameters. After analyzing the main influence factors and their effect laws during the BTT flight phase, a coupling control strategy called “decrease angle of attack—rolling fast—increase the angle of attack again” was proposed. Simulation studies were conducted to investigate the feasibility of the proposed control strategy for the hypersonic vehicle. The simulation results demonstrate that the proposed control strategy lowers the control requirement of yaw channel, lowers the probability of being out of control in the BTT flight phase, and increases the reliability of the control system.]]></description>
<pubDate>2017/9/12 10:09:50</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[WANG Peng]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>WANG Peng</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201704019]]></guid><cfi:id>200</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Unmanned aerial vehicle relative navigation method based on robust high degree cubature filtering]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201704021]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Due to the strong-nonlinearity and non-Gaussianity of the UAV (unmanned aerial vehicle) relative navigation system, the accuracy of the traditional relative navigation filter, which is designed based on the Kalman filtering algorithm, decreases or even diverge. In view of the advantages of HCKF (high degree cubature Kalman filter) and MCKF (maximum correntropy Kalman filter) in coping with nonlinear problems and non-Gaussian problems, respectively, the measurement update equation was modified by the measurement update method of MCKF, and the traditional measurement update problem was recast as a linear regression problem. In addition, the Gaussian assumption of the measurement noise was avoided, the system nonlinearity and measurement noise non-Gaussianity were solved at the same time. The simulation was conducted, and the simulation results indicated that RHCF is superior to HCKF and MCKF. Hence, the effectiveness of the proposed algorithm is verified.]]></description>
<pubDate>2017/9/12 10:09:50</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[JIN Hongxin<sup>1,2</sup>, YANG Tao<sup>1</sup>, WANG Xiaogang<sup>3</sup>, LU Xin<sup>2</sup> and LI Pu<sup>1,2</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>JIN Hongxin<sup>1,2</sup>, YANG Tao<sup>1</sup>, WANG Xiaogang<sup>3</sup>, LU Xin<sup>2</sup> and LI Pu<sup>1,2</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201704021]]></guid><cfi:id>199</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Evaluation indexes and requirements of wind tunnel based virtual flight testing for flight control systems]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201704022]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In order to determine the FCS (flight control system) performances which the WTBVFT (wind tunnel based virtual flight testing) can evaluate, and lay the foundations for designing the WTBVFT evaluation methods, the flight performance indexes and flight quality indexes of FCSs which WTBVFT can perform the work of evaluation were proposed according to the features of WTBVFT; the evaluation capability differences among the WTBVFT, the HILS (hardware-in-the-loop simulation) and the flight tests were compared; the differences of evaluation results between WTBVFT and free flight caused by the features of WTBVFT were analyzed; from the aspects of testing, data processing, and the performance determination, the specific requirements of the WTBVFT evaluation methods for evaluating the above indexes were proposed and the evaluation requirement differences among the WTBVFT, HILS, and flight tests were compared.]]></description>
<pubDate>2017/9/12 10:09:50</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[HUANG Min, WANG Zhongwei, GUO Zhenyun and NIU Yaobin]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>HUANG Min, WANG Zhongwei, GUO Zhenyun and NIU Yaobin</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201704022]]></guid><cfi:id>198</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Numerical simulation of periodic unsteady flow by harmonic balance method]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201704026]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The harmonic balance method is one of the computational methods in frequency domain with a high computational efficiency, which has won  special attention in present numerical studies of unsteady flow, and it has an obvious advantage especially for periodic unsteady flow problems. A harmonic balance method was used to simulate the forced pitching oscillation of the HBS(hyper ballistic shape) in different conditions, and then the coefficient of force and moment versus angle of attack were rebuilt. A comparison was made with the time domain method to investigate the performance of the harmonic balance method. Results show that the harmonic balance method is applicable to simulate middle and small amplitude pitching, and the computing time won’t be effected by the frequency. Therefore, the harmonic balance method has obvious advantage for problems with a long period.]]></description>
<pubDate>2017/9/12 10:09:50</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[CHAI Zhenxia, LIU Wei, LIU Xu and YANG Xiaoliang]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>CHAI Zhenxia, LIU Wei, LIU Xu and YANG Xiaoliang</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201704026]]></guid><cfi:id>197</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Exergy analysis of the potential working about the heat of cooling fuel for scramjet at supercritical pressures]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201704027]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Coolant flow rate of fuel for scramjet exceeds stoichiometric flow rate in the high flight Mach number. In order to lower the coolant flow rate of fuel and implement the matching between coolant flow rate and stoichiometric flow rate, the potential working for the cooling fuel was analyzed by exergy method. The  properties of the cooling of fuel at supercritical pressures determines the quantity of exergy. The exergy was calculated according to the distribution of scramjet wall’s temperature, scramjet wall’s heat flux, and the exergy equilibrium equation was given. It is concluded that the heat of scramjet wall is 562.4 kW and the exergy is 541.3 kW when the maximum temperature of scramjet wall is 1200 K. It is also concluded that the potential working is lowered while the coolant flow rate of fuel is increased and the output temperature of fuel is increased, and the potential working is not changed when the output pressure of fuel is increased.]]></description>
<pubDate>2017/9/12 10:09:51</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LI Xinchun and WANG Zhongwei]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LI Xinchun and WANG Zhongwei</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201704027]]></guid><cfi:id>196</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[One-dimensional analysis for performance of ejector with precooling]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201703001]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[According to the one-dimension design theory of ejector, cooling the secondary flow before it enters into the mixing chamber can promote the eject efficiency and increase the eject coefficient, but flow loss is brought with the addition of precooler, so the performance evaluation of ejector is necessary. Looking on the eject system with precooler, the effect of precooler on the performance of system was analyzed through the onedimension theory, and the effects of the intensifying effect of precooling and the weakening effect of resistance on eject efficiency were analyzed emphatically. The research results indicate that: the precooler brings intensifying effect of precooling and weakening effect of resistance to eject system, and the cross section area and heat transfer area of the precooler are the dominating factors; cross section area of the precooler has a critical value, when the cross section area is bigger than the critical value, the eject performance improves with the increase of heat transfer area, otherwise it worsens; the eject performance of the equivalent pressure mixing scheme is better than that of the equivalent area mixing scheme, the eject coefficient of the former is 60% higher than the latter; precooling improves the eject performance effectively, especially for the equivalent area mixing scheme, the performance is improved by 35.5%.]]></description>
<pubDate>2017/7/9 11:57:44</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[ZHANG Jianqiang<sup>1,2</sup>, WANG Zhenguo<sup>1,2</sup>, LI Qinglian<sup>2</sup>, XU Wanwu<sup>2</sup> and ZOU Jianjun<sup>2</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>ZHANG Jianqiang<sup>1,2</sup>, WANG Zhenguo<sup>1,2</sup>, LI Qinglian<sup>2</sup>, XU Wanwu<sup>2</sup> and ZOU Jianjun<sup>2</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201703001]]></guid><cfi:id>195</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Effect of gravity gradient on dynamical characteristics of very large flexible space structures in orbit]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201703002]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Space solar power station is a kind of space structure with large size and high flexibility. It is far larger than the previous spacecraft in size, which results in new phenomena and new problems on the study of dynamical characteristics. The kilometerscale dumbbell model was studied. The Hamilton’s dynamical model on orbit was established under the effect of gravity gradient. The symplectic Runge-Kutta method was used with different combinations of parametrical values to obtain dynamical responses. By comparing the simulation results, the quantitative relationships were determined respectively between the size of space structure and the effect of gravity gradient on orbital motion and attitude motion. It is found that: due to the gravity gradient, the coupling phenomenon between attitude motion and elastic vibration occurs; the attitude motion has great influence on the external envelope curve of elastic vibration response, while the period of it is changed by elastic vibration.]]></description>
<pubDate>2017/7/9 11:57:45</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[MU Ruinan<sup>1</sup>, TAN Shujun<sup>2</sup> and WU Zhigang<sup>1,2</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>MU Ruinan<sup>1</sup>, TAN Shujun<sup>2</sup> and WU Zhigang<sup>1,2</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201703002]]></guid><cfi:id>194</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[A survey of gliding guidance methods for hypersonic vehicles]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201703003]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The basic problem of gliding guidance for hypersonic vehicles was proposed, and the difficulties of complicated multiple constraints, maneuver requirements, and parameter perturbation in the course of gliding guidance were analyzed. The corresponding research status at home and abroad was surveyed, and the problems were also pointed out. On this basis, the key problems required to be solved at present in the research of gliding guidance for hypersonic vehicles were presented, and the research hotspots in the methods of future gliding guidance were also pointed out. ]]></description>
<pubDate>2017/7/9 0:00:00</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[PAN Liang<sup>1</sup>, XIE Yu<sup>1</sup>, PENG Shuangchun<sup>1</sup>, XU Mingliang<sup>2</sup> and YUAN Tianbao<sup>3</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>PAN Liang<sup>1</sup>, XIE Yu<sup>1</sup>, PENG Shuangchun<sup>1</sup>, XU Mingliang<sup>2</sup> and YUAN Tianbao<sup>3</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201703003]]></guid><cfi:id>193</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Differential transformation-based trajectory trackingguidance scheme for hypersonic reentry vehicle]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201703004]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Concentrating on the hypersonic reentry guidance under multiple constraints, a full-state nominal trajectory tracking guidance scheme was proposed by applying the differential transformation approach to the optimal feedback control. In the  period of the online closed-loop guidance scheme based on the recedinghorizon control, the nominal trajectory tracking problem was transformed into a state regulator problem of the associated linear time-varying system, and then into a two-point boundary value problem by utilizing the optimal control theory. The differential transformation approach was suggested for the optimal feedback control, avoiding the time-consuming and numerical instabilities of conventional methods. Numerical simulation results validate that the proposed guidance scheme is robust to state dispersions and model uncertainties, providing a reference for engineering design. ]]></description>
<pubDate>2017/7/9 11:57:45</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LIU Li<sup>1,2</sup>, YANG Leping<sup>1</sup> and CAI Weiwei<sup>3</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LIU Li<sup>1,2</sup>, YANG Leping<sup>1</sup> and CAI Weiwei<sup>3</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201703004]]></guid><cfi:id>192</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Parameters prediction method of underwater grid fins during the procedure of dynamic expansion]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201703009]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Based on the kinetic model of underwater grid fins during the procedure of dynamic expansion, a prediction method  was developed, which took the motion parameters at typical expansion points as the design input. The hydrodynamic moment used in the kinetic model was fitted by the values obtained in steady hydrodynamic conditions with specific expansion angles. A modified factor in consideration of the relative velocity was included as well. By comparing with the results obtained by unsteady numerical simulations and the underwater vehicle experiment data, the prediction method is verified, which can provide a design reference for the optimum proposal of the underwater grid fins and the analysis of nonsynchronization expansion.]]></description>
<pubDate>2017/7/9 11:57:45</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[BAO Wenchun, QUAN Xiaobo, LI Yan, CHENG Shaohua and WANG Zhanying]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>BAO Wenchun, QUAN Xiaobo, LI Yan, CHENG Shaohua and WANG Zhanying</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201703009]]></guid><cfi:id>191</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Numerical simulation on parachute′s infinite mass inflation dynamics]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201703010]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[To analyze the supersonic opening performance of the parachute in Mars reentry environment, the coupling dynamic models between compressible fluid and flexible structure of parachute were solved on the basis of the arbitrary Euler-Lagrange penalty function method and the multi-material arbitrary Lagrange Euler algorithm. The evolution of 3D shape of DGB(disk gap band) parachute during supersonic inflation was simulated, and the structural dynamic behaviors of canopy fabric were predicted. The drag area and coefficients were compared with the wind tunnel data, and the inflation performance of parachute and the influence of fore-body were analyzed. Finally, the wake of unsteady fluid and distribution of shock wave around supersonic parachute were investigated. The results show that: the DGB parachute is well inflated without serious collapse; as the increase of Mach numbers, the drag coefficients gradually decrease, along with the increase of the inflation time, which brings into correspondence with the test results, and proves the validity of the proposed method.]]></description>
<pubDate>2017/7/9 11:57:45</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[GAO Xinglong<sup>1,2</sup>, ZHANG Qingbin<sup>1</sup>, GAO Qingyu<sup>1</sup> and TANG Qiangang<sup>1</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>GAO Xinglong<sup>1,2</sup>, ZHANG Qingbin<sup>1</sup>, GAO Qingyu<sup>1</sup> and TANG Qiangang<sup>1</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201703010]]></guid><cfi:id>190</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[High-precision torque control for magnetically suspended reaction flywheel]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201703025]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In order to improve the torque-output precision of the magnetically suspended reaction flywheel, compensation methods were proposed respectively to attenuate the undesirable torque ripple caused by nonideal back electromotive force waveform and commutation in classical control of brushless direct current motor. The real-time back electromotive force was estimated according to the rotor position and speed in order  to obtain the  reference current, the pulse width modulation duty cycle was calculated in the torque controller to compensate the torque ripple caused by the nonideal back electromotive force. The theoretical derivation was analyzed, methods of modulation of the non-commutation phase during low-speed range and modulation of the switching-out phase during high-speed range were presented on the basis of the characteristics respectively. Also, a calculation method of the commutation time was given. The experimental results show that the proposed methods can achieve an effective compensation.]]></description>
<pubDate>2017/7/9 11:57:47</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[FENG Jian, LIU Kun and FENG Yushu]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>FENG Jian, LIU Kun and FENG Yushu</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201703025]]></guid><cfi:id>189</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Wind tunnel based virtual flight testing system and key technologies for the evaluation of flight control system]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201702001]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In order to provide a guide for specific investigations on WTBVFT(wind tunnel based virtual flight testing) techniques, the test system and key technologies of WTBVFT for the evaluation of FCS (flight control system) were analyzed. Based on the deficiencies of the traditional FCS evaluation methods, the advantages of WTBVFT for evaluation of FCS were analyzed. According to the common constitution of attitude control loop and guidance control loop used by FCS, the test system and working principle of WTBVFT for FCS evaluation were presented. The main differences between the WTBVFT system and the hardware-in-the-loop simulation system were analyzed. The key technologies of WTBVFT for FCS evaluation were also analyzed, including WTBVFT evaluation methods, aircraft model design technique, FCS modification technique, and model support technique.]]></description>
<pubDate>2017/5/11 0:00:00</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[HUANG Min, WANG Zhongwei and GUO Zhenyun]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>HUANG Min, WANG Zhongwei and GUO Zhenyun</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201702001]]></guid><cfi:id>188</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Gliding trajectory optimization with multiple objectives and complicated constraints for hypersonic vehicles]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201702002]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[A multi-objective gliding trajectory optimization scheme was proposed for hypersonic vehicles with complicated constraints, such as aerodynamic heating, overload, dynamic pressure, control variables, waypoint, no-fly zones, and terminal states. The pole-transformed motion equations were deduced to simplify some of the constraints and to avoid the singularity of the traditional motion equations. Furthermore, the physical programming was employed to convert the multi-objective optimization problem to a single optimization objective problem considering the designer′s preference. Based on the multi-phase Gauss pseudospectral method, the optimal control problem of the single objective trajectory optimization problem was converted to a nonlinear programming problem. Results demonstrate that the algorithm can generate optimal gliding trajectories satisfying all the complicated constraints while the designer′s preference can be taken into consideration.]]></description>
<pubDate>2017/5/11 16:56:54</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[XIE Yu, PAN Liang, GU Xueqiang and CHEN Jing]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>XIE Yu, PAN Liang, GU Xueqiang and CHEN Jing</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201702002]]></guid><cfi:id>187</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Multi-model sensor management for space-basedmissile warning satellite system]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201702003]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In order to improve the performance of space-based missile warning system in tracking multi-target, the latitude-zone scan mode and target-group track mode were proposed for the scanner and tracker respectively. Based on these modes, the scan sensor and track sensor management algorithms were proposed. For the multi-model sensors, their working mode, the scanning frequency, the measurement error and the field-of-view differ from each other, an observation tracking Cramer-Rao formula was derived. Finally, a multi-model senor management algorithm based on the above methods was proposed. Results show that the proposed algorithm has a higher tracking accuracy for multi-target than the system in traditional working mode. ]]></description>
<pubDate>2017/5/11 16:56:54</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LIU Bing, YI Taihe, SHEN Zhen and YI Dongyun]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LIU Bing, YI Taihe, SHEN Zhen and YI Dongyun</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201702003]]></guid><cfi:id>186</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[1/5 dynamic scaled model design of  launch vehicle]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201702004]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The design of dynamic scale model is one of the most important parts in the scale model test which is an effective approach to obtain dynamic characteristics of large launch vehicle. Taking the launch vehicle as the object, the similarity relationships for each part were derived on the basis of the structural components of the launch vehicle. Transverse dynamic similarity relationships of the launch vehicle were derived by taking advantage of the consistent similarity in respect of transverse stiffness and mass. Taking the actual processing and manufacturing conditions into consideration, the restrictions of similarity coefficient for transverse stiffness and mass were analyzed. According to the relationships and the restrictions above, a 1/5 dynamic scale model was designed and its similarity of dynamic characteristics was verified through the numerical analysis of finite element. The verification result shows that the 1/5 scale model gets a high-level similarity with the prototype in terms of dynamic characteristics, and the method can be effectively applied to the design of dynamic scale model for launch vehicle.]]></description>
<pubDate>2017/5/11 16:56:55</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LIU Caizhi<sup>1,2</sup>, TANG Guojin<sup>1</sup> and ZHOU Lilin<sup>1</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LIU Caizhi<sup>1,2</sup>, TANG Guojin<sup>1</sup> and ZHOU Lilin<sup>1</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201702004]]></guid><cfi:id>185</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Numerical simulation on fault in gas and liquid lines of spacecraft propulsion system]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201702005]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In order to investigate the failure mechanism, dynamic changing law and the effect of leakage and blockage fault of spacecraft propulsion system, a dynamic simulation of some pressure-fed propulsion system was conducted based on the modular model library previously. The leakage and blockage fault of gas pressurization lines were simulated with the method of Realizable k-ε model and one-dimensional compressible duct model respectively. The leakage and blockage fault simulation for propellant lines were carried out with the finite element state-variable model and variable flow coefficient model respectively. The dynamic simulation of the propulsion system was carried out and some interesting results have been obtained as follows. Firstly, due to the leakage and blockage fault of gas pressurization lines, the pressure boost couldn′t meet the need of operational state, resulting in the propellant inadequacy and pressure drop in propellant lines. Secondly, because of the leakage and blockage fault in propellant lines, the mixture radio would deviate from the designed ones, resulting in the sliding down of the propulsion system performance. Although both of the leakage and blockage fault would make the propulsion system performance slide down, there are differences between the two faults. Firstly, due to the blockage fault, the upstream pressure of faulty component is substandard and less propellant is consumed. Secondly, due to the leakage fault, the upstream pressure of leaking object is lower than normal value and too much propellant is consumed.]]></description>
<pubDate>2017/5/11 16:56:55</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[NIE Yao, CHENG Yuqiang and WU Jianjun]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>NIE Yao, CHENG Yuqiang and WU Jianjun</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201702005]]></guid><cfi:id>184</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Research on the drag mode of space net system]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201702006]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[For the problem in the mission design demands, the influence of the drag mode on the deployment property of the space net system was investigated. The dynamic model was set up and verified by ground test result. Evaluation criterion of space net system was set up to meet the mission demands and the impact that the drag mode brought in was studied through a finite element method. The simulation models, in which mass of the net and initial projection energy were kept the same, were built based on the finite segment approach for four and six points drag modes. Simulation result of the evaluation criterion indicates that the system flight performance indexes and the dynamic evaluation criterions are improved in the six points drag mode, the energy utilization rate and system reliability, however, show minor decrease.]]></description>
<pubDate>2017/5/11 16:56:55</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[GAO Qingyu, ZHANG Qingbin, TANG Qiangang and FENG Zhiwei]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>GAO Qingyu, ZHANG Qingbin, TANG Qiangang and FENG Zhiwei</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201702006]]></guid><cfi:id>183</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[New regional and parametric reliability sensitivities and their computational methods]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201702007]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Based on the variance-based global reliability sensitivity index, new regional and parametric sensitivity indices were defined respectively to measure how the sensitivity indices of the whole inputs change when the distribution range of one input is changed or its variance is decreased. Then these two proposed indices were described by PCC (Pearson correlation coefficient) between the unconditional failure indicator and its pick-frozen replication. Based on the transformation, two methods based on PCC were proposed to compute the proposed regional and parametric sensitivity indices. One method was based on Monte Carlo method and iterating sampling, whereas the other one was based on IS (importance sampling) and reusing the samples without extra computational cost, so the computational efficiency of the second method was much higher. The feasibility of the proposed regional and parametric indices, the accuracy and high efficiency of the proposed methods were demonstrated by the results of several examples.]]></description>
<pubDate>2017/5/11 16:56:55</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LI Baoyu<sup>1,2</sup>, ZHANG Leigang<sup>2</sup>, SHI Jiao<sup>2</sup> and YU Xiongqing<sup>1</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LI Baoyu<sup>1,2</sup>, ZHANG Leigang<sup>2</sup>, SHI Jiao<sup>2</sup> and YU Xiongqing<sup>1</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201702007]]></guid><cfi:id>182</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Simulation on hypervelocity impact characteristics of stuffed corrugation-cored sandwiches]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201702008]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Based on the demand of the spacecraft protection against the orbital debris, numerical simulation of a new designed stuffed corrugation-cored sandwich under hypervelocity impact was carried out. The hypervelocity impact process was obtained, and thereby the perforation of the sandwich and the characteristics of the debris cloud were analyzed. It can be seen that the phenomenon of stuffed corrugation-cored sandwich under hypervelocity impact is similar to that of Whipple structure, but the head velocity of the debris cloud is lower and the expansion velocity and expansion angle is larger. With the impact velocity increasing from 3 km/s to 10 km/s, the size of the sandwich perforation increases accordingly and the shape of the perforation becomes more irregular. Furthermore, the epoxy stuffed in the sandwich absorbs most impact energy of the debris while the front plate and the corrugation core absorb less energy. The research can provide some references for the design of orbital debris shield.]]></description>
<pubDate>2017/5/11 16:56:55</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[ZHOU Hao<sup>1</sup>, GUO Rui<sup>1</sup>, NAN Bohua<sup>2</sup> and LIU Rongzhong<sup>1</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>ZHOU Hao<sup>1</sup>, GUO Rui<sup>1</sup>, NAN Bohua<sup>2</sup> and LIU Rongzhong<sup>1</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201702008]]></guid><cfi:id>181</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Impact of satellite platform attitudes′ error on  imaging geometric quality of TDICCD]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201702015]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The research of influence on TDICCD camera′ s imaging geometric quality can contribute to improving quality by advancing the design requirements of the platform. The quantitative relation of the platform attitude error and the imaging geometric quality based on the image point displacement was studied. The model of imaging parameters′ error caused by attitude error was built, including the error of image motion velocity, the drift angle correction and integral time. The relation between imaging parameters′ error and image motion combined with the strict geometric imaging model was deduced. The quantitative model of the geometric quality indexes under the influence of image motion was established, including angle distortion, length distortion, pixel resolution and positioning accuracy. The perfectly quantitative chain from attitude error to geometric quality indexes was created. The simulation experiment was conducted and the results indicate that the main influencing factor of geometric quality is the error of yaw angle.]]></description>
<pubDate>2017/5/11 0:00:00</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[WU Zhaocong<sup>1</sup>, YANG Fan<sup>1</sup>, WU Yuan<sup>1</sup>, ZHU Jun<sup>2</sup> and HAN Xingzi<sup>2</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>WU Zhaocong<sup>1</sup>, YANG Fan<sup>1</sup>, WU Yuan<sup>1</sup>, ZHU Jun<sup>2</sup> and HAN Xingzi<sup>2</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201702015]]></guid><cfi:id>180</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Robust unscented Kalman filter for calculating reentry vehicle trajectory]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201701001]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The difficulties that unscented Kalman filter encounters when it is introduced in reentry vehicle trajectory were investigated. These difficulties include abnormal measurement, the inaccuracy of measurement random error model and dynamic model. The current study uses an adaptive robust filter that can produce the estimation of equivalent weight flexibly according to measurement noise and state noise,  can distinguish abnormal measurement from normal measurement, and can estimate the variance of Wiener model self-adaptively. The simulated results testified that the filter is easy to implement and can reduce the bad influences derived from inaccuracy of measurement random error model and dynamic model.]]></description>
<pubDate>2017/3/7 11:55:43</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LI Chan, ZHANG Shifeng and ZHANG Lijun]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LI Chan, ZHANG Shifeng and ZHANG Lijun</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201701001]]></guid><cfi:id>179</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Spacecraft attitude maneuver algorithm design based on adaptive second-order terminal sliding mode]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201701002]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In order to solve the attitude maneuver problem of rigid spacecraft, an adaptive second-order terminal sliding mode control algorithm was designed. A terminal sliding mode surface was designed to guarantee that the system states can converge to the original point along the sliding surface in finite time; a second-order terminal sliding mode controller was designed to overcome chattering, and an adaptive estimation parameter was adopted to compensate the external disturbances. The Lyapunov function methods proved that the designed algorithm can guarantee that the closedloop system is practically finite-time stable. The simulation results show that this algorithm can achieve fast response and high accuracy, can effectively restrain the system chattering and the external disturbance, and has important scientific significance and engineering value.]]></description>
<pubDate>2017/3/7 11:55:43</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[RAN Dechao, NI Qing, SHENG Tao and CHEN Xiaoqian]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>RAN Dechao, NI Qing, SHENG Tao and CHEN Xiaoqian</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201701002]]></guid><cfi:id>178</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Coupled design of landing window and point return orbit for manned lunar landing mission]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201701003]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[For the manned lunar landing mission that lands on the moon high latitude destination and  returns to earth high latitude recovery field, a  design of moon landing window and point return orbit is  coupled in complexity, so it is one of the key technologies in the engineering task. In view to task demands and engineering constraints, the mathematical models for finding lands window and designing point return orbit were established in the first place; Secondly, by solving the rules of landing window and  point return orbit parameters, the coupled geometrical principle was analyzed; Taking a mission that lands on Sinus Iridium in 2025 for example, the strategy of coupled design landing window and the point return orbit were given, which was provided by validation example. The verification by commercial Software STK(system tool kits, by AGI company) of simulation results is correct, the proposed strategy is a simple and precise method for planning manned lunar landing mission, which can be used in the future manned lunar landing mission directly.]]></description>
<pubDate>2017/3/7 11:55:43</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[HE Boyong<sup>1</sup>, LI Haiyang<sup>1</sup>, SHEN Hongxin<sup>2</sup> and PENG Qibo<sup>3</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>HE Boyong<sup>1</sup>, LI Haiyang<sup>1</sup>, SHEN Hongxin<sup>2</sup> and PENG Qibo<sup>3</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201701003]]></guid><cfi:id>177</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Calculation of satellite′s initial attitude using multi-sensor intercalibration]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201701005]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[After the satellite is separated from the upper stage, the initial attitude is not learned about since the attitude sensors are not  valid for the measurement. In order to solve this problem, an initial attitude calculation method using multi sensors’ intercalibration was designed. The kinematic equation was set firstly, and then the first available attitudes measured by star sensor as well as gyro’s angular velocity were prepared. The nonlinear equation was solved by using the trust region algorithm; meanwhile the attitude was obtained from backward to forward; the analog sun vector detector’s information was used to revise the deduction; a convenient method translating the attitude from the sun to the earth was put forward; sun vector was connected to star sensor’s information. The deduction result is consistent with injection attitude of rocket. Simulation result on the ground was compared with the real attitude in orbit, validating the correctness of simulation model. The result provides support for the design of satellite and the procedure design and improvement of flight.]]></description>
<pubDate>2017/3/7 11:55:44</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LI Xiaoyue<sup>1,2</sup>, XIONG Shujie<sup>1</sup> and LIN Baojun<sup>1</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LI Xiaoyue<sup>1,2</sup>, XIONG Shujie<sup>1</sup> and LIN Baojun<sup>1</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201701005]]></guid><cfi:id>176</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Observable degree analysis of gyroscope error coefficients for inertially stabilized platforms self-calibration]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201701007]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Aiming at the observable degree of gyroscope error coefficients for inertially stabilized platforms self-calibration system, a novel observable degree analytical method was presented according to the definition of observability. The highest order of measurement derivative in the expression of a state analytical solve was defined as the state observable degree. Based on this, the observability of inertially stabilized platforms self-calibration system was analyzed, highlighting the observable degrees of gyroscope error coefficients. The observable states of system were presented, and it was proved that the observable degrees of the gyroscope biases to sensitivity along the input axes were worst. Simulation results validated the correctness and validity of this approach, which provides a reference for the design of torquing scheme of inertially stabilized platforms self-calibration system.]]></description>
<pubDate>2017/3/7 11:55:44</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[DING Zhijian, CAI Hong and HUANG Shuai]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>DING Zhijian, CAI Hong and HUANG Shuai</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201701007]]></guid><cfi:id>175</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Error parameters identification for inertial navigation platform based on centrifuge test]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201701008]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In order to identify the error parameters of inertial navigation platform in the centrifuge testing, a 6-position identification scheme was developed. The non-linear model of the inertial navigation platform for the identification was established, and the extended Kalman filter algorithm was applied to estimate the error parameters. The correlation coefficients among the error parameters calculated with the estimation error covariance matrix in the filter were used to analyze the observability of the system. The minimum sum of all correlation coefficients was considered as the optimization criterion, and then the genetic algorithm was utilized to obtain the optimal position combination. The simulation results show that the scheme is valid to identify all the error coefficients connected with the higherorder acceleration with high precision. ]]></description>
<pubDate>2017/3/7 11:55:44</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[XU Yongfei and ZHANG Shifeng]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>XU Yongfei and ZHANG Shifeng</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201701008]]></guid><cfi:id>174</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Reconstruction of attitude control system of launch vehicle based on linear programming under servo mechanism fault]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201701009]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Servo mechanism fault of engine brings challenge to the reliability and safety of attitude control system for the new generation launch vehicle, a research on control reconstruction strategy is needed urgently. Aiming at this problem, a control allocation method for the deflection angle reconstruction was proposed. The problem of deflection angle allocation under servo mechanism fault was transformed into the problem of 1norm single objective constrained optimization, and then it was translated into the standardized linear programming model solved by simplex algorithm finally. Simulation results show that the attitude control system can be completely reconstructed by the proposed method under servo mechanism fault, each deflection angle does not reach its saturation value, so the validity of the method is proved.]]></description>
<pubDate>2017/3/7 0:00:00</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[CHENG Tangming, LI Jiawen and TANG Guojin]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>CHENG Tangming, LI Jiawen and TANG Guojin</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201701009]]></guid><cfi:id>173</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Longitudinal integrated guidance and control scheme for hypersonic vehicle in glide phase]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201701010]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[A longitudinal integrated guidance and control scheme for the hypersonic vehicle in glide phase was designed based on the dynamic surface control method and the sliding mode control theory. The translational  rotational dynamic and kinematical equations in the longitudinal plane were denoted; the desired velocity slope angle was derived based on the predictor corrector of the longitudinal range; the relations of the velocity slope angle, angle of attack, and the pitch rate were established. The dynamic surface control, the terminal sliding model and the second-order sliding mode control methods were adopted to implement the longitudinal integrated guidance and control scheme; the commanded angle of attack and elevon fins were analytically solved by using the GHV’s aerodynamic model having partial derivative matrix forms. The effectiveness and robustness of the newly proposed longitudinal integrated guidance and control scheme was validated. Moreover, the characteristics of flight phases before and after the quasi equilibrium glide phase were discussed and the problems with respect to the guidance and control system design were analyzed.]]></description>
<pubDate>2017/3/7 11:55:44</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[WANG Jianhua, LIU Luhua, WANG Peng and TANG Guojian]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>WANG Jianhua, LIU Luhua, WANG Peng and TANG Guojian</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201701010]]></guid><cfi:id>172</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Domain-decomposed parallel computation methods for unstructured dynamic mesh]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201701013]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[For parallel simulation of the unsteady flow field with moving boundary, a domain-decomposed computation procedure was designed based on the spring analogy method, and the METIS software was introduced to repartition the original grids. With the research of 1-to-1 interface communication styles and realization, the unstructured dynamic mesh solver was parallelized based on the message passing interface. The test shows that the solver has high parallel efficiency, and the module of mesh deforming has significant effect on the parallel performance.]]></description>
<pubDate>2017/3/7 11:55:44</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[CHENG Xinghua, LIU Wei and ZHANG Lilun]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>CHENG Xinghua, LIU Wei and ZHANG Lilun</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201701013]]></guid><cfi:id>171</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Sequential approximate optimization method]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201701015]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[As more and more high precise time-consuming models are revealed into optimization procedure, general intelligence optimization algorithm cannot get a desirable result in feasible computing cost. The developing sequential approximate optimization approach is aimed to overcome this drawback by introducing the approximate model in the optimization procedure, which adds infill points sequentially to search the promising areas, has made it more and more practical technique for time-consuming engineering optimization. An overview of the sequential approximate optimization algorithm and its core techniques were given, which can expend the application of the algorithm. Finally, some relevant improved methods and new developmental trends concerning SAO(sequential approximate optimization) were presented.]]></description>
<pubDate>2017/3/7 11:55:44</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[HU Fan, WU Zeping, WANG Donghui and ZHANG Weihua]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>HU Fan, WU Zeping, WANG Donghui and ZHANG Weihua</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201701015]]></guid><cfi:id>170</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Fast circle filter HOG for car detection from aerial images]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201701021]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In general, cars are rectangular shape in the aerial images, so the histograms of orient gradient over the whole sliding window were computed to find the primary gradient direction and to estimate the orientation of the car in the window, and the detection window was rotated according to the car’s orientation to perform classification. A cascaded boosting classifier and the HOG (histograms of orient gradient) features in the proposed car detection method were employed. To efficiently compute the HOG features in the rotated window, a fast HOG features extraction method based on CFHOG (circle filter based histograms of orient gradient), which was more efficient than the classical HOG extraction method based on integral histograms. In addition, lookup tables are used to speed up the calculation of the orientation partition and magnitude. A set of experiments on real images prove the applicability and high efficiency of the proposed car detection method.]]></description>
<pubDate>2017/3/7 11:55:45</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[SU Ang, ZHANG Yueqiang, YANG Xia and YU Qifeng]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>SU Ang, ZHANG Yueqiang, YANG Xia and YU Qifeng</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201701021]]></guid><cfi:id>169</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Effects of umbrella slot on the  structure integrity of solid rocket motor grain with large aspect ratio]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201701023]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[To improve the structural integrity of solid rocket motor grain with large aspect ratio, based on three-dimensional viscoelastic finite element method and taking into account of the temperature load and pressure load, the structural response of a solid rocket motor with large aspect ratio was analyzed, the effects of the umbrella slot and its location on maximum Von Mises strain of the grain were studied, and the variations of the maximum Von Mises strain of the umbrella slot with its width, depth and radius ratio were discussed when the umbrella slot was in the middle of the grain. The results show that the Von Mises strain is reduced when the umbrella slot is in the middle of the grain; increasing the width, depth or choosing the best radius ratio can reduce the maximum Von Mises strain of the umbrella slot. The conclusions are beneficial for designing the grain configuration of solid rocket motor.]]></description>
<pubDate>2017/3/7 11:55:45</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[SHEN Zhibin<sup>1</sup>, JIANG Renwei<sup>1</sup> and ZHI Shijun<sup>2</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>SHEN Zhibin<sup>1</sup>, JIANG Renwei<sup>1</sup> and ZHI Shijun<sup>2</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201701023]]></guid><cfi:id>168</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Indentation experiment of composite sandwich structure with metal foam core]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201701029]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Sandwich structure with metal foam core is a newly emerged sandwich structure in recent years, and will be widely used in near space flight vehicle, navigation and automobile fields due to its high flexural rigidity and strength, multifunction. Theoretical analysis and experimental studies on the indentation response, damage modes, deformation mechanism and failure mechanism of the composite sandwich panel with fibre-reinforced polymer face and aluminum foam core under the action of rigid spherical-end indenter were conducted. Study results show that the load-indentation response is a combined consequence of the individual responses of the sandwich components, their structural interactions and the indenter properties. The failure models of the sandwich panel under the spherical-end cylindrical indenter can be summarized as matrix cracking, fiber fracture, face/core debonding, the yield and shear of the aluminum foam.]]></description>
<pubDate>2017/3/7 11:55:45</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[WANG Xinzhu<sup>1,2,3</sup>, ZHOU Xiong<sup>3</sup>, ZHU Bingjie<sup>4</sup> and PENG Xianghe<sup>3</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>WANG Xinzhu<sup>1,2,3</sup>, ZHOU Xiong<sup>3</sup>, ZHU Bingjie<sup>4</sup> and PENG Xianghe<sup>3</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201701029]]></guid><cfi:id>167</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[A numerical method for two-dimensional nonlinear transient inverse heat conduction problems for orthotropic material]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201701030]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[A sequential functional specification method was adopted to identify the surface heat flux in a two-dimensional inverse heat conduction problem for an orthotropic solid. The inverse problems were solved with the combination of the finite control volume method, the  Newton-Raphson method, and the concept of future time step.The undetermined heat flux at each time step was denoted as one of the unknown variables in a set of nonlinear equations, which was solved by an iterative process. Results show that the estimated values  agree well with the exact values in the examples, which proves that this method is an accurate, stable, and efficient one, thus it can be used to determine the surface heat flux in two-dimensional nonlinear inverse heat conduction problems.]]></description>
<pubDate>2017/3/7 11:55:45</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[CHEN Minkang<sup>1</sup>, DU Tao<sup>2</sup>, SU Xue<sup>3</sup> and CHEN Weifang<sup>3</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>CHEN Minkang<sup>1</sup>, DU Tao<sup>2</sup>, SU Xue<sup>3</sup> and CHEN Weifang<sup>3</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201701030]]></guid><cfi:id>166</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Multiple impulsive trajectory optimization of satellite formation reconfiguration under J<sub>2</sub> perturbation]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201806001]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Arming at the formation reconfiguration problem for the elliptic reference orbit under J<sub>2</sub>perturbation, a multiple impulsive trajectory optimization strategy was developed on the basis of the Gauss variation equation and with the objective function of minimal fuel consumption. A relative dynamics equation using the orbital element difference was derived, in which the J<sub>2</sub> perturbation and the coupling effects between in-plane and out-of-plane relative movements were considered. The hybrid approach of the genetic algorithm and the sequence quadratic programming was proposed to optimize the total velocity increment. The simulation results show that the hybrid approach is effective, and can obtain the feasible solution efficiently. Since the J<sub>2</sub> perturbation and elliptic reference orbit are considered in the study, the approach has some reference significance for the trajectory optimization of space mission.]]></description>
<pubDate>2019/1/17 15:43:44</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[WANG Youliang<sup>1,2,3</sup>, ZHENG Jianhua<sup>1,2,3</sup> and LI Mingtao<sup>1,2,3</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>WANG Youliang<sup>1,2,3</sup>, ZHENG Jianhua<sup>1,2,3</sup> and LI Mingtao<sup>1,2,3</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201806001]]></guid><cfi:id>165</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Fluid-thermal-structural study of integrated algorithm for aerodynamically hypersonic heated leading edges]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201806002]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[A fluid-thermal-structural integrated method was presented based on finite volume method for hypersonic aeroheating-structural-thermal interaction. A system of unified integral equations was developed as the control equations for physical process of aero-heating and structural heat transfer. The whole physical field was discretized by using an up-wind finite volume method, which avoids the fussy data exchange and computational complexity in coupling method. To demonstrate its capability, applications for fluid-thermal-structural analysis of hypersonic ow over 2D stainless steel cylinder in steady and unsteady states, were performed and discussed. The numerical results show that the maximum temperature of about 648 K occurs at the stagnation point of stainless steel cylinder in a steady state and the objective physical processes in a good agreement with measured values in unsteady state. Compared with the coupling method, the integrated algorithm has shown a better stability with lesser griddependence，which provides theoretical and technical support for the thermal protection system of hypersonic vehicles.]]></description>
<pubDate>2019/1/17 15:43:44</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LI Jiawei, WANG Jiangfeng, YANG Tianpeng and JI Weidong]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LI Jiawei, WANG Jiangfeng, YANG Tianpeng and JI Weidong</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201806002]]></guid><cfi:id>164</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Application of different roughness shapes in inducingsupersonic boundary layer transition]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201806003]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In order to investigate the differences of the transition mechanisms between four roughness shapes, a fifth-order WCNS scheme was used to simulate the supersonic flat-plate boundary layer transition induced by the square, cylinder, diamond and hemisphere roughness elements at Mach 4.20. Results show that the square roughness element has the longest separated region where the absolute instability is formed, thus resulting in the earliest transition. The diamond roughness element has the widest separated region and leads to the widest turbulent wake region. The cylinder and hemisphere roughness elements are less effective in inducing transition compared with the square and diamond roughness elements.]]></description>
<pubDate>2019/1/17 0:00:00</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[ZHOU Yunlong<sup>1</sup>, LIU Wei<sup>1</sup> and WU Dong<sup>2</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>ZHOU Yunlong<sup>1</sup>, LIU Wei<sup>1</sup> and WU Dong<sup>2</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201806003]]></guid><cfi:id>163</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Research and application of improved elasticity-based mesh deformation method based on geometry constraints]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201806004]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Aimed at the problem that the current elasticity-based mesh deformation method always cannot control some poor elements suffering “negative volume” and extreme distortion, the volume and the extruding constraints on modulus of elasticity were introduced to solve above shortages and a modified elasticity-based method based on these geometry constraints was presented. Combined with Patrick mesh quality measure, the differences between the modified method and the classical method were fully analyzed by testing a 3D cubic model with three types of motion or deformation in wide-range, such as rotation, translation, and stretch. The modified method was applied to simulate the plunging motion of NACA0012 airfoil and stretching deformation of wing. Results show this modified method can improve the robustness of elasticity-based method by constraining poor elements in wide-range of motion or deformation, thus providing a better support for solving the unsteady flow  problems.]]></description>
<pubDate>2019/1/17 15:43:45</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[ZHANG Bin, FENG Zhiwei, YANG Tao, PENG Wuyu and ZHANG Qingbin]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>ZHANG Bin, FENG Zhiwei, YANG Tao, PENG Wuyu and ZHANG Qingbin</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201806004]]></guid><cfi:id>162</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Structural design and mechanical deformation simulation of flexible inflatable wing for miniature missile]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201806005]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Based on NACA2412 airfoil, the improved stress expression model established by considering the influence of distribution mass can achieve the allowable range of inflation pressure of the flexible film wings. The results show that smaller the size of the flexible wing inflatable units are, the greater the allowable range of the inflation pressure can be. ABAQUS/CAE software was used for simulating the stress and deformation of flexible aerated wing under different inflation pressure conditions. The unique way of warping of asymmetric airfoil after inflating was found. The risk points of flexible skin were determined. The typical lines were used to analyze the local mechanical properties of the inflatable wing. The improved inflatable wing with surface coating obtained a good effect of improving the structure mechanical properties.]]></description>
<pubDate>2019/1/17 15:43:45</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LIU Longbin, JIA Yicong, WEI Yuan, HU Fan and ZHANG Shifeng]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LIU Longbin, JIA Yicong, WEI Yuan, HU Fan and ZHANG Shifeng</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201806005]]></guid><cfi:id>161</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Optimal sensor placement for aeroservoelastic analysis of high-aspect-ratio flexible aircraft]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201806006]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[An advanced criterion of optimal sensor placement was proposed for aeroservoelastic analysis of high-aspect-ratio flexible aircraft based on classical sensor placement index. The trace of observability Gramian matrix was proved to be the vibration energy, and the dimension of the ellipsoid was introduced as the geometric mean of eigenvalues, a high efficient simplified method was given as a computational approach. Different modes and sensors placement influences on the system were evaluated though the properties of H<sub>2</sub> norm in connection with system impulse response, a balance between the low and the high frequency modes was achieved to guarantee the dominant of low order vibration and avoid overflow. Considering the bending moment of the body, the bend and torsion of the wings, the different sensor placement indexes were evaluated. Results shows that the sensor placement can be set accurately and effectively, while different modes can also be fully weighted and reflected by the proposed criterion. This method can be used as an optimal tool to set the sensor placement through the whole flight track and it has a great value in engineering application.]]></description>
<pubDate>2019/1/17 15:43:45</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[YANG Weiqi<sup>1,2</sup> and YANG Hui<sup>2</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>YANG Weiqi<sup>1,2</sup> and YANG Hui<sup>2</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201806006]]></guid><cfi:id>160</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Influence of secondary flow ejection on the performance of conformal asymmetric nozzle]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201806007]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The reasonability of the structure design of aircraft engine and after-body directly affects the components matching and performance of the engine. The numerical analysis for the internal and external field characteristics of the conformal asymmetric nozzle of flying-wing unmanned aerial vehicle in the typical flight condition was carried out by adopting the 3D Reynolds-averaged N-S equation and k-ωSST turbulence model. The thrust performance of afterbody nozzle and also the variation trend of the 3D flow characteristics against the blow-down ratio of secondary flow were obtained. The results show that under a fixed blow-down ratio of the engine nozzle, the main flow field characteristics of the after-body nozzle can be effectively improved by reasonably optimizing the secondary flow channel and increasing the blow-down ratio of secondary flow；when the flow rate of secondary flow and main flow is within the range of 0.2% to 1.86%, the changing range of nozzle axial thrust coefficient is about 3%. Overexpansion of the engine′s main flow is weakened to a certain extent and thrust loss of the engine is decreased. Therefore, the blow-down ratio of secondary flow has great influence on the performance of the after-body nozzle of unmanned aerial vehicle.]]></description>
<pubDate>2019/1/17 15:43:45</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[MA Song<sup>1,2</sup>, TAN Jianguo<sup>1</sup>, ZHANG Zhiwei<sup>2</sup>, ZHU Wei<sup>1,2</sup> and JIANG Hao<sup>2</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>MA Song<sup>1,2</sup>, TAN Jianguo<sup>1</sup>, ZHANG Zhiwei<sup>2</sup>, ZHU Wei<sup>1,2</sup> and JIANG Hao<sup>2</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201806007]]></guid><cfi:id>159</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Effects of gas liquid ratio on the combustion of liquid centered swirl coaxial injector]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201806008]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In order to analyze the influence of gas liquid ratio on the combustion of liquid centered swirl coaxial injector, hot tests were conducted with a combustion gas generator under different gas liquid ratio. This combustion gas generator was equipped with liquid centered swirl coaxial injector. The results show that there exist three combustion conditions: stable combustion, transition from stable combustion to low frequency combustion instability and low frequency combustion instability. The low frequency combustion instability is not related to the oscillation of the supply system. It occurs because the triple flame moves away from the injection panel, when the triple flame arrives at the point of the impinging sprays, the stability of the triple flames decrease rapidly, making the flame front oscillating in the recirculation zone.]]></description>
<pubDate>2019/1/17 15:43:45</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[KANG Zhongtao<sup>1,2,3</sup>, LI Qinglian<sup>2,3</sup>, ZOU Jianjun<sup>2,3</sup> and CHENG Peng<sup>2,3</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>KANG Zhongtao<sup>1,2,3</sup>, LI Qinglian<sup>2,3</sup>, ZOU Jianjun<sup>2,3</sup> and CHENG Peng<sup>2,3</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201806008]]></guid><cfi:id>158</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Estimation of initial error and guidance instrumentation error based on nonlinear model]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201806009]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The accurate estimation of the initial error and the guidance instrumentation error plays a key role in the precision assessment of the maneuvering launched vehicle, so a new estimation method based on nonlinear model was proposed. The platform initial angle error was transformed into the orientation error. The true apparent acceleration was accurately calculated by using the fixed point iteration method. Then, the trajectory parameters of the truth launch coordinate were represented by a nonlinear function with the initial error and the guidance instrumentation error. A nonlinear model was constructed by using the exterior trajectory measurements. This model can simultaneously estimate the initial error, the guidance instrumentation error, the measurement systematic error, and the time-zero deviation between telemetry data and exterior data, and it can avoid the linear approximation of the initial error. The Bayes MAP (maximum a posterior) estimation is given to obtain the optimal estimation of these errors by using the nonlinear model and the prior information, and it is proved to be convergent. Experimental results show that the proposed method improves the estimation accuracy of the initial error and the guidance instrumentation error when compared with the linear method and other nonlinear method. Furthermore, the proposed method can also achieve the selfcalibration between different measurements.]]></description>
<pubDate>2019/1/17 15:43:45</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LI Dong<sup>1</sup>, WEI Chao<sup>1</sup> and ZHOU Xuanying<sup>2</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LI Dong<sup>1</sup>, WEI Chao<sup>1</sup> and ZHOU Xuanying<sup>2</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201806009]]></guid><cfi:id>157</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Method of rotating-calculating magnetic gradient tensor]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201806026]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In order to obtain the magnetic gradient tensor of magnetic target, the method of rotating-calculating magnetic gradient tensor was proposed. The enough magnetic gradient data can be measured by rotating the magnetic gradiometer about the vertical axis, and it is used to calculate the magnetic gradient tensor. The difference of the magnetic gradient tensor between theoretical value and measurement value was used as the reference, and the rotation angle, inclination angle and baseline length of calculation model were optimized. The influence of three-axis pointing error of magnetometer on the calculation result of magnetic tensor was analyzed. The simulation results show that the proposed method is effective in calculating the magnetic gradient tensor. There is little difference between the calculated value and the theoretical value.]]></description>
<pubDate>2019/1/17 0:00:00</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[JIA Wendou<sup>1</sup>, LIN Chunsheng<sup>1</sup>, CHEN Chunhang<sup>1</sup> and ZHAI Guojun<sup>2,3</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>JIA Wendou<sup>1</sup>, LIN Chunsheng<sup>1</sup>, CHEN Chunhang<sup>1</sup> and ZHAI Guojun<sup>2,3</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201806026]]></guid><cfi:id>156</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Design and experiment of a new type explosive null gate with detonating cord]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201806027]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In order to enhance the stability of the explosive null gate and reduce the requirements of the groove filling process in the applications,  the method which used the detonating cord to replace the partial groove charge structure was proposed by taking the gap null gate as the research object. The combination experiments of detonating cord with different size parameters, groove charge and null gate gap were carried out, and the optimal filling material combination which has simple filling process and more stable control ability of the signal channel was expected to be obtained. Results indicate that the stability and reliability of the explosive null gate device can be guaranteed, and the parameters of the explosive null gate consisting of detonating cord be properly configured.]]></description>
<pubDate>2019/1/17 15:43:46</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[DING Liangliang<sup>1</sup>, LI Zhenduo<sup>1,2</sup>, LI Xiangyu<sup>1</sup> and LU Fangyun<sup>1</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>DING Liangliang<sup>1</sup>, LI Zhenduo<sup>1,2</sup>, LI Xiangyu<sup>1</sup> and LU Fangyun<sup>1</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201806027]]></guid><cfi:id>155</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Midcourse and terminal guidance handover window for interceptor against near space  hypersonic target]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201805001]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The equations describing the relative dynamics was established by using a modified polar coordinate. The capture region of the typical guidance law for intercepting the hypersonic target was derived, and the optimal intercept geometry which is the zero effort miss steering was derived. The missile speed, the missile height, the characteristics of seeker and terminal capture region were analyzed. Then, the influence factors, application, features of handover window and calculation flow were analyzed. Taking the pure proportional navigation guidance law as an example, the mid-course and terminal guidance handover window and the zero effort interception handover region were described quantitatively. Finally a simulation was performed to verify the feasibility of the handover window.]]></description>
<pubDate>2018/11/15 16:12:21</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[WANG Huaji<sup>1</sup>, LEI Humin<sup>1</sup>, ZHANG Dayuan<sup>2</sup>, ZHOU Jin<sup>1</sup> and SHAO Lei<sup>1</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>WANG Huaji<sup>1</sup>, LEI Humin<sup>1</sup>, ZHANG Dayuan<sup>2</sup>, ZHOU Jin<sup>1</sup> and SHAO Lei<sup>1</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201805001]]></guid><cfi:id>154</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Simulation model for sabot discard using dynamic mesh technique]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201805002]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Aimed at the changing progress that sabot moves from contacting to the projectile′s body to doing 6-DOF(degree of freedom) motion revolving around sabot′s centroid, a simulation model for sabot′s discard based on motion separation and coupling the fluid control equation and 6-DOF equation by using dynamic mesh was proposed. Taking APFSDS (armor piercing fin stabilized discarding sabot) for example, this model was used to simulate the sabot′s discard under different Mach numbers and analyze the variations of dynamic coefficients of sabot and projectile body. Simulation results show that the bigger the discard Mach number is, the closer to projectile′s body the sabot′s trajectory is, and also the shorter the discard time is, but the further the discard distance is. The validity of the proposed sabot′s discard simulation model was verified by a comparison with the experiment data. ]]></description>
<pubDate>2018/11/15 16:12:21</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LI Xiangping, LU Junyong, FENG Junhong, DU Peipei and WU Xiaokang]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LI Xiangping, LU Junyong, FENG Junhong, DU Peipei and WU Xiaokang</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201805002]]></guid><cfi:id>153</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Photogrammetry for relative pose measurement of satellite and rocket]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201805003]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[A method of measuring the relative pose of satelliterocket separation based on vision was presented. For the camera parameters were known, the camera was installed on the carrier rocket, and more than six cooperation signs were fixed on the satellite. The cameras can take pictures of the cooperation signs in real time. Based on the basic principle of monocular vision pose estimation, the relative pose relationship between satellite and rocket was solved by combining efficient perspectivenpoint with orthogonal iteration. The simulation experiment and the semiphysical simulation experiment prove the feasibility and accuracy of the proposed method.]]></description>
<pubDate>2018/11/15 16:12:21</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[DING Shaowen<sup>1,2</sup>, CHEN Hao<sup>3</sup>, WANG Jie<sup>1,4</sup> and ZHANG Xiaohu<sup>1,5</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>DING Shaowen<sup>1,2</sup>, CHEN Hao<sup>3</sup>, WANG Jie<sup>1,4</sup> and ZHANG Xiaohu<sup>1,5</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201805003]]></guid><cfi:id>152</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Influence of air torque  on average torque equilibrium attitude of space station]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201805004]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The models of attitude movement were established in order to study the influence factors of ATEA(average torque equilibrium attitude) of the space station. The influence of the air torque on the ATEA(average torque equilibrium attitude) of the space station was analyzed. The models of dynamic and control of the space station were established. A typical proportion derivative controller was used. Groups of 24 ATEA were separately obtained under two conditions. The results show that the air torque exhibits a significant influence on ATEA. In order to keep the ATEA of the space station, periodicity of control torque need to be provided. The momentum unloading and accumulating effects of the space station induced by air torque cannot be neglected.]]></description>
<pubDate>2018/11/15 16:12:21</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LIU Jianghui, LI Haiyang and ZHANG Yakun]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LIU Jianghui, LI Haiyang and ZHANG Yakun</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201805004]]></guid><cfi:id>151</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Study on viscoelastic constitutive model of solid propellant and its implementation in finite element method]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201805005]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The viscoelastic Poisson′s ration master curve of solid propellant was established on the basis of the time-temperature equivalence principle and WLF equation, and then the viscoelastic constitutive model of solid propellant was proposed. The viscoelastic constitutive model in incremental form was deduced on the basis of the incremental finite element method  and by adopting the fully explicit integration method. The constitutive model was realized in finite element software by using the consistent tangent stiffness acquired according to the programming rules of user subroutine in MSC.Marc. The stress-strain mechanical response of solid propellant grains was analyzed by using the viscoelastic and the elastic Poisson′s ration under solidification process and ignition pressurization process. Furthermore, the effects of different kind of Poisson′s rations on the stress-strain field were compared. The method and result can provide a reference for the structural integrity analysis of engine grain.]]></description>
<pubDate>2018/11/15 16:12:22</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[CUI Huiru, SHEN Zhibin and LI Haiyang]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>CUI Huiru, SHEN Zhibin and LI Haiyang</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201805005]]></guid><cfi:id>150</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Test trajectory optimization design subjected to high dynamic pressure simulation]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201805006]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[To solve the high dynamic pressure testing problem while ballistic missile is in flight testing with high-altitude launch site, a test trajectory design method for simulating high dynamic pressure condition was proposed. Firstly, aimed at the actual characteristics of launch site, the dynamic model of wreckage reentry and the impact area boundary model were established. Then, the high dynamic pressure simulated condition was transferred to a process constraint, and a powered phase united optimization strategy was proposed. Based on the adaptive simulated annealing algorithm, three test trajectories meeting different high dynamic pressure simulated conditions and all constraints were designed separately, meanwhile the impact area adjusted program was generated correspondingly, and its feasibility was demonstrated. Results illustrates that the maximal dynamic pressure occurs in the first stage, the maximal negative angle of attack in the first stage contributes to improve the maximal dynamic pressure greatly; the warhead impact point constraint of test trajectory can be guaranteed by adjusting launching azimuth and the pitch program angle of the second and the third stage at the same time.]]></description>
<pubDate>2018/11/15 16:12:22</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[ZHOU Xiang, ZHENG Wei, WANG Peng and WANG Lei]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>ZHOU Xiang, ZHENG Wei, WANG Peng and WANG Lei</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201805006]]></guid><cfi:id>149</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Flexible formation control of stratospheric airships based on path following]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201805007]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Dynamics model of the stratospheric airship during floating was established, and the model was linearized using linear perturbation theory based on the assumption which the flight altitude is constant. A flexible leaderfollower formation control method for stratospheric airships based on path following was proposed, in which the leader and followers track the reference trajectory respectively through velocity and heading control. Linear formation and circular control of three stratospheric airships were simulated and the simulation results show that the control accuracy of the path following method is high while the formation can operate stably, and the collision among airships can be avoided.]]></description>
<pubDate>2018/11/15 16:12:22</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[YANG Xixiang<sup>1,2</sup> and ZHANG Jiashi<sup>1</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>YANG Xixiang<sup>1,2</sup> and ZHANG Jiashi<sup>1</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201805007]]></guid><cfi:id>148</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Application of free-form deformation technique forRAE2822 airfoil optimization design]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201805008]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[FFD (free-form deformation) technique was applied to achieve the parameterization of RAE2822 transonic airfoil. Then the method of DoE (design of experiment) was used to obtain the sample values of design parameters by CFD (computational fluid dynamics) numerical simulation. Lastly, the optimization analysis was carried out by using the Kriging surrogate model and MIGA, NLPQL optimization algorithm. The CFD values with optimized design parameters were regarded as the final results. The results show that the FFD parametric method can directly realize deformation on airfoil mesh. Compared with original airfoil, the lift-to-drag ratio of optimized airfoil increases by 57.2%, therefore, the proposed method is feasible and effective.]]></description>
<pubDate>2018/11/15 16:12:22</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[CHEN Lili, GUO Zheng and HOU Zhongxi]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>CHEN Lili, GUO Zheng and HOU Zhongxi</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201805008]]></guid><cfi:id>147</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Ground impact test and its simulation of space net]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201805025]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[A ground impact test of space net was designed and conducted. Then the simulation of ground test was established and the comparisons of ground test and simulation results were analyzed. The impact force and tether tension of space net during impact process were investigated based on the simulation. The results show that: the simulation results agree well with the ground test results, which indicates the reliability of simulation model; the constraining tension of space net during impact process can well make the space net close up and wrap the target; the flexibility of space net can well mitigate the impact response and the tethers in impact area are more likely to fracture during impact process.]]></description>
<pubDate>2019/1/21 16:09:53</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[ZHEN Ming, YANG Leping and ZHANG Qingbin]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>ZHEN Ming, YANG Leping and ZHANG Qingbin</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201805025]]></guid><cfi:id>146</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[VCFEM microscopic method for evaluating effective mechanical properties of composite solid propellants]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201804009]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The RVE (representative volume element) models were generated by using the equalcircle optimal circular packing scheme to characterize the microstructure of solid propellants. In order to obtain the influence laws of volume fraction and component material on effective modulus and Poisson′s ratio, a numerical analysis method for evaluating effective mechanical properties of solid propellants was developed by combining the VCFEM (Voronoi cell finite element method) and the homogenization method. The displacement result of a symmetric numerical example was compared with the traditional finite element method for validating the effectiveness of this method. The relative error between the two methods is less than 5%. The analysis efficiency is improved by using VCFEM, because it needs fewer elements. Moreover, the RVE models of different microstructures were calculated. It is found that with the increase of particle volume fraction, the enhancement effect of particles is more obvious. And the matrix material has a more significant influence than the inclusion material on the effective mechanical properties. ]]></description>
<pubDate>2018/9/17 11:14:35</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[SHEN Liulei<sup>1</sup>, SHEN Zhibin<sup>1</sup>, LI Jingyu<sup>2</sup> and LI Haiyang<sup>1</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>SHEN Liulei<sup>1</sup>, SHEN Zhibin<sup>1</sup>, LI Jingyu<sup>2</sup> and LI Haiyang<sup>1</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201804009]]></guid><cfi:id>145</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Characteristics of plasma synthetic jet actuator array in parallel]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201804010]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Due to its superiorities of high exhaust speed, wide frequency band and rapid response, the plasma synthetic jet actuator has shown wide and promising application prospects in high-speed flow control. On account of the weak control authority and small affected area of single actuator, a parallel actuator array was investigated. A parallel microsecond-grade pulse power supply was developed to achieve a three-path discharge. The power supply shows good stability with and without the load at 1000 Hz working frequency. As the capacitor increases, the temperature of the plasma arc increases. The air in the actuator chamber is heated more prominently. So the speed of the jet rises. As the frequency increases, the jet speed decreases due to a lower breakdown voltage. The parallel actuators can be controlled independently by manipulating the trigger signals, which makes the parallel actuators more flexible than the serial actuators. The phase of the actuator was shown to be controlled accurately by the trigger signal.]]></description>
<pubDate>2018/9/17 11:14:35</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[WANG Lin<sup>1</sup>, ZHOU Yan<sup>1</sup>, LUO Zhenbing<sup>1</sup>, XIA Zhixun<sup>1</sup>, SHAO Tao<sup>2</sup> and DENG Xiong<sup>1</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>WANG Lin<sup>1</sup>, ZHOU Yan<sup>1</sup>, LUO Zhenbing<sup>1</sup>, XIA Zhixun<sup>1</sup>, SHAO Tao<sup>2</sup> and DENG Xiong<sup>1</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201804010]]></guid><cfi:id>144</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Optimal control allocation method for entry vehicle based on PWPF modulator]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201804012]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[For the entry vehicle equipped with RCS (reaction control system) and rudder, an optimal control allocation method based on PWPF (pulsewidth pulse-frequency) modulator was proposed. By transforming the discrete control signal of RCS into the continuous quantity, the control allocation problem was constructed as a quadratic programming problem. And the active-set method was used to solve the quadratic programming problem. Then, the on-off signal of RCS was obtained by using the discrete method and PWPF modulator. Compared with the mixed integer programming problem, the quadratic programming problem is easier to be solved, which is favorable for on-board computing. The proposed method has the fault-tolerant ability by reconstituting the quadratic programming problem.]]></description>
<pubDate>2018/9/17 11:14:36</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[WANG Tao<sup>1,2</sup>, CAO Xiaorui<sup>3</sup>, ZHANG Hongbo<sup>1</sup> and TANG Guojian<sup>1</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>WANG Tao<sup>1,2</sup>, CAO Xiaorui<sup>3</sup>, ZHANG Hongbo<sup>1</sup> and TANG Guojian<sup>1</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201804012]]></guid><cfi:id>143</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Analytical solution for free flight trajectory considering earth nonspherical gravitation perturbation]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201804013]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In order to solve the fast calculation of the free trajectory considering the effects of the earth non-spherical gravitation, the differential equations of motion under the earth gravitation including the J<sub>2</sub>-perturbation were established in the non-orthogonal coordinate system, and the differential equations of motion under disturbing gravity were established in the orbital coordinate system. The acceleration of upward disturbing gravity was equivalent to the mass deviation of the earth, and introduced into the standard elliptical orbit. The differential equations under J<sub>2</sub>-perturbation were modified, and the parameters of the position and velocity were calculated under the analytical solution. The simulation results show that the analytic solution has a higher efficiency, and the position error of impact point is within 20 meters. The analytic solution satisfies the requirement of the real-time guidance and orbit forecast.]]></description>
<pubDate>2018/9/17 11:14:36</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[CHANG Xiaohua]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>CHANG Xiaohua</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201804013]]></guid><cfi:id>142</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Error analysis and optimal maneuver trajectory design of the point target location based on a moving visual platform]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201804014]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The point target location based on a moving visual platform was studied. After introducing the visual location method, the sight-line restriction of the collinear equation was analyzed. The error impact of view-line angle vector to the point target location was deduced in the view-line associated coordinate system. Multitime measurements were also analyzed in the location error analysis. Based on the minimization of the target location error, the optimal maneuver trajectory of the observer platform was designed. Using a method that is simpler and easier to understand, the results obtained from the proposed method are the same as those from the method by maximizing the determinant of the Fisher information matrix. Simulations and tests were performed, and results show that the target location error analysis and the platform optimal maneuver trajectory design are valid.]]></description>
<pubDate>2018/9/17 11:14:36</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[ZHANG Hongliang, YU Xianguo and WANG Zi]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>ZHANG Hongliang, YU Xianguo and WANG Zi</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201804014]]></guid><cfi:id>141</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Bayesian combination forecasting for fatigue reliability of aircraft structures]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201804016]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In practical engineering, it is often necessary to use models to describe and analyze problems. However, uncertainty exists in the models. There are many models that can describe the same phenomenon, such as the multiple fatigue analysis models. In order to solve the problem of fatigue reliability of aircraft structures, a combination forecasting method based on Bayesian model averaging was proposed by considering three kinds of crack propagation models. Three random crack propagation models were established by using the crack propagation data of aircraft structures under three stress levels. Considering the uncertainty of the model parameters, the Bayesian model averaging method was used to combine the three models. The reliability of the structure was analyzed based on the combined model. The combined model was used to analyze the fatigue reliability of aircraft structure, which can improve the robustness of the results. In addition, considering the uncertainty of the model parameters, more reasonable predictive distribution of crack propagation as well as the reliability can be obtained. Examples and analysis results are given to show the feasibility of this method. ]]></description>
<pubDate>2018/9/17 11:14:36</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[YUAN Xiukai and LIU Wenjie]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>YUAN Xiukai and LIU Wenjie</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201804016]]></guid><cfi:id>140</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Analysis on design factors of hypervelocity fragment launcher using strong detonation drive]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201804023]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In order to explore the relations between design factors of the launcher and performance of the produced hypervelocity fragment, the AUTODYNTM-employed numerical simulation towards launch process was performed repeatedly under the orthogonal experiment design framework. Design factors include explosive type, diameter ratio of charge,  material type, thickness, taper angle and radius of the top close to charge chamber for liner part were considered. Multiple target launcher designs were demonstrated:  three of which were capable to provide the red copper fragment with the mass of 1.563 g, the aluminum fragment with the velocity of 11.649 km/s and the aluminum one with the kinetic energy of 856 kJ respectively;  two of which can produce compact cylindrical fragments with the mass over 1 g and velocity over 11km/s simultaneously. The associated experimental validation was confirmed as well and a further analysis of the design factors was made which explains how they were related to the mass, velocity and kinetic energy of generated fragment.]]></description>
<pubDate>2018/9/17 11:14:36</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[XING Boyang<sup>1</sup>, LIU Rongzhong<sup>1</sup>, GUO Rui<sup>1</sup>, CHEN Liang<sup>1</sup>, YANG Yongliang<sup>1</sup>, ZHAO Bobo<sup>1,2</sup> and GAO Ke<sup>1</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>XING Boyang<sup>1</sup>, LIU Rongzhong<sup>1</sup>, GUO Rui<sup>1</sup>, CHEN Liang<sup>1</sup>, YANG Yongliang<sup>1</sup>, ZHAO Bobo<sup>1,2</sup> and GAO Ke<sup>1</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201804023]]></guid><cfi:id>139</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Line target homing method of parafoil system]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201803001]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Aimed to the large dispersion situation of the rocket booster or sub-stage falling to the ground without controlling, the line target homing method of parafoil system was put forward. The calculation model of rectangular boundary was established, and the contraction regional analysis of two kinds of homing methods namely point target and target line was performed. The influence of parafoil homing ability and the scattered boundary characteristics of falling area on homing performance were analyzed, and the corresponding homing strategy was obtained. A solution for setting up multiple landing areas in larger dispersion area was proposed. Finally, the dynamics and control model was established and the line target homing process was simulated. Satisfactory results are obtained，which shows that the proposed method has some reference value to the project.]]></description>
<pubDate>2018/7/11 12:40:20</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[TENG Haishan<sup>1,2</sup>, TANG Guojian<sup>2</sup>, LIU Tao<sup>1</sup> and ZHANG Zhang<sup>1</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>TENG Haishan<sup>1,2</sup>, TANG Guojian<sup>2</sup>, LIU Tao<sup>1</sup> and ZHANG Zhang<sup>1</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201803001]]></guid><cfi:id>138</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Differential game guidance laws against active defense aircraft]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201803002]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Evasion and pursuit guidance laws for the missile attacking the defense aircraft were derived based on the differential game theory. Three guidance laws which are optimalpursuit guidance law, evasion-pursuit guidance law and composite guidance law respectively were derived using a traditional cost function by defining different weight coefficients. If the missile uses the optimalpursuit guidance law, it can be intercepted easily. When the missile uses the evasionpursuit guidance law, the zero miss distance between the missile and aircraft will increase sharply; thus the missile fails to attack the aircraft easily. When the missile uses the composite guidance law, it is hard to choose the reasonable weighting parameters. To overcome these deficiencies, two new guidance laws were investigated and the sufficient conditions for the missile winning the game were analyzed. The two new guidance laws were verified by the nonlinear simulation and the results show that the proposed guidance laws can help the attacking missile evade the defender and attack the aircraft successfully.]]></description>
<pubDate>2018/7/11 12:40:20</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[SUN Qilong, QI Naiming, ZHAO Jun and LIN Haiqi]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>SUN Qilong, QI Naiming, ZHAO Jun and LIN Haiqi</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201803002]]></guid><cfi:id>137</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Analysis on wing deformation modes of hypersonic morphing aircraft]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201803003]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Aiming at improving the range of wingbody combination aircraft at hypersonic flow conditions, the aerodynamic characteristics and wing efficiency of morphing tactical missile with different deformation modes at Mach number from 3 to 8 were studied. The NavierStokes equations were used to simulate the flow field, and the lifttodrag ratio, wing efficiency, stability and controllability of different deformation modes as telescopic, variable sweep and twodimensional folding were compared. Results show that under the condition of supersonic and hypersonic flow, the variable sweep wing mode improves the lifttodrag ratio significantly, and at the same time, it has excellent wing efficiency and stability and controllability. The mode performs best at the Mach number from 3 to 8. The conclusion can offer some valuable guidance to the research and application of hypersonic morphing aircraft aerodynamic configuration.]]></description>
<pubDate>2018/7/11 12:40:20</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[PENG Wuyu<sup>1</sup>, YANG Tao<sup>1</sup>, TU Jianqiu<sup>2</sup>, FENG Zhiwei<sup>1</sup> and ZHANG Bin<sup>1</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>PENG Wuyu<sup>1</sup>, YANG Tao<sup>1</sup>, TU Jianqiu<sup>2</sup>, FENG Zhiwei<sup>1</sup> and ZHANG Bin<sup>1</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201803003]]></guid><cfi:id>136</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Calculation of coupled motion dynamic derivatives of swept flight terminal sensitive projectile]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201803004]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[A novel swept flight terminal sensitive projectile was taken as a computation object, and the method to deal with simulation of the complex angular motion based on the Euler rotation theorem and a spherical sliding meshing technique was proposed. The modification value of the projectile′s angular velocity at each time step was interpolated out through applying the Rodriguez transformation matrix, and it was further allocated to the sliding meshing zone. Based on the method, the influences on pitching combination dynamic derivatives and lift coefficients under various Mach numbers made by the projectile′s rolling motion were analyzed after solving and identifying the unsteady aerodynamic parameters. Results indicate that: the proposed method can eliminate the accumulative errors in the calculation of attitude angles effectively and can realize the accurate simulation under arbitrary given angular motion; the projectile′s rolling motion generate significant influences on the identification results of pitching combination dynamic derivatives and lift coefficients, and the influence of the pitching coupled effect should be taken into account in the process of calculating the projectile′s pitching motion and stability analysis.]]></description>
<pubDate>2018/7/11 12:40:20</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[CHEN Liang, LIU Rongzhong, GUO Rui, YANG Yongliang, XING Boyang, GAO Ke and ZHAO Bobo]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>CHEN Liang, LIU Rongzhong, GUO Rui, YANG Yongliang, XING Boyang, GAO Ke and ZHAO Bobo</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201803004]]></guid><cfi:id>135</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Frequency domain method for computing dynamic derivatives of airframe/propulsion integrative vehicle]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201803005]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[With the help of the unsteady Etkin aerodynamic model, the harmonic balance method to calculate the dynamic derivatives of complicated configuration was applied. The dynamic derivatives solved by harmonic balance method agree well with the results of time domain method and experimental data, which verified the correctness of codes and the reliability of the harmonic balance method. The harmonic balance method was applied to compute the dynamic derivatives of X-51 hypersonic airframe/propulsion integrative vehicle namely WR-A. A comparison was made with the time domain method to verify the ability of the harmonic balance method for the numerical simulation of unsteady flows around the complicated model and the ability of the computing dynamic derivatives. Results show that even for the vehicle WR-A of the complex configuration, the harmonic balance method was computationally accurate and efficient.]]></description>
<pubDate>2018/7/11 0:00:00</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[CHAI Zhenxia, LIU Wei, LIU Xu and YANG Xiaoliang]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>CHAI Zhenxia, LIU Wei, LIU Xu and YANG Xiaoliang</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201803005]]></guid><cfi:id>134</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Investigation of mean velocity measurement for low Reynolds number wall-bounded flow using Pitot tubes]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201803006]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The numerical investigation of two main factors, velocity shear and wall proximity effect, which affects mean velocity measurement for low Reynolds number wall-bounded flow using Pitot tubes, was carried out. Their effects were separated through careful numerical simulation and cases were run for each of them respectively for error analysis. The simulation results show that: for velocity shear, the result of current work basically agrees with that of related literature, however, the nondimensional streamline shift does not asymptotically approach to a constant value; noticeable wall vicinity effect can be found within 5 tube diameters to the wall, and errors are decreasing within 1 tube diameter to the wall. Comparisons were made among the numerical solutions in this work and the corrections being used in the literature, and the new corrections based on simulation results of current work were given in the end.]]></description>
<pubDate>2018/7/11 12:40:20</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[ZHANG Huaibao<sup>1</sup>, WANG Jingyu<sup>1</sup>, Bailey Sean C.C.<sup>2</sup>, WANG Guangxue<sup>1</sup> and DENG Xiaogang<sup>3</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>ZHANG Huaibao<sup>1</sup>, WANG Jingyu<sup>1</sup>, Bailey Sean C.C.<sup>2</sup>, WANG Guangxue<sup>1</sup> and DENG Xiaogang<sup>3</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201803006]]></guid><cfi:id>133</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Fast attitude maneuver control method of micro flight vehicle]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201803007]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In order to fulfill the attitude control mission of micro flight vehicle delivered from a certain kind of ballistic missile, a fast attitude maneuver control approach based on the GPM (Gauss pseudospectral method) was proposed. Firstly, the accurate attitude control model was established and the coupling torque term of the reaction wheels was taken into account. Secondly, the GPM was adopted to obtain the optimal attitude trajectories. Moreover, a quasisliding mode controller was designed to track the optimal trajectories. Numerical simulation results demonstrate the optimality of the attitude maneuver trajectories obtained by using the GPM， the good performances of the quasisliding mode controller in tracking the optimal trajectories, and the good effect in rejecting the external disturbance torque.]]></description>
<pubDate>2018/7/11 12:40:20</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LIU Chengguo<sup>1</sup>, YU Xiang<sup>2</sup>, LIU Kun<sup>2</sup> and LIU Jiaqi<sup>1</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LIU Chengguo<sup>1</sup>, YU Xiang<sup>2</sup>, LIU Kun<sup>2</sup> and LIU Jiaqi<sup>1</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201803007]]></guid><cfi:id>132</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Inverse Poisson integral semiparametric approach of estimating airborne gravity systematic error and downward continuation]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201803008]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The existing systematic errors processing method of airborne gravity demands external gravity data, but many areas do not have external gravity data. However, semiparameter model can estimate the systematic errors without external data. Firstly, the systematic errors were modeled by using natural spline function. Then the compensation least squares method was used to estimate the parameter and the natural spline function. The smooth parameter was used to balance them. More importantly, the generalized cross validation method to determine the smooth parameter does not need prior information. Therefore, the semiparameter model was applied in the inverse Poisson integral to estimate systematic errors and downward continuation in one step. The numerical test results show that the inverse Poisson integral and least square collocation cannot estimate the systematic errors. The regularization method based on the inverse Poisson integral can reduce systematic error effect. The semiparameter combine inverse Poisson integral model can estimate the systematic errors and improve downward continuation accuracy at the same time without external gravity data.]]></description>
<pubDate>2018/7/11 12:40:20</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[ZHAO Qilong<sup>1,2</sup>, LI Jiancheng<sup>1</sup>, XU Xinyu<sup>1</sup> and YU Nan<sup>1</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>ZHAO Qilong<sup>1,2</sup>, LI Jiancheng<sup>1</sup>, XU Xinyu<sup>1</sup> and YU Nan<sup>1</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201803008]]></guid><cfi:id>131</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Design method of scale model for large composite spatial frame]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201803009]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Scale model test is an effective approach to obtain mechanical characteristics or response of large composite spatial frame, in which the design of scale model is one of the most important parts. Large composite spatial frame was taken as the object. The limitation of the existing traditional methods was elaborated; based on the discrete similarity, the equational analysis method combing the finite element method was proposed; the similarity relationship for static response and dynamic characteristics of large composite spatial frame was deduced by this method; the 1/5 scale model of a composite keel was designed by the proposed method and was verified through experiments. The verification result shows that the proposed method and the deduced similarity relationships can be used to guide the scale model test of large composite spatial frame.]]></description>
<pubDate>2018/7/11 12:40:20</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[ZHOU Lilin<sup>1</sup>, LIAN Yongzheng<sup>2</sup>, LIU Caizhi<sup>2</sup> and LI Daokui<sup>1</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>ZHOU Lilin<sup>1</sup>, LIAN Yongzheng<sup>2</sup>, LIU Caizhi<sup>2</sup> and LI Daokui<sup>1</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201803009]]></guid><cfi:id>130</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Design and implementation of two-dimensional matrix convolution based on vector processor]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201803011]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In order to accelerate the computational speed of convolution neural network model and facilitate the implementation of largescale neural network model in embedded microprocessor, the FT-matrix2000 vector processor architecture was taken as the research background. Through the analysis of the multi-core vector processor architecture and convolution neural network algorithm, a data layout scheme was proposed in which a smaller convolution kernel data was placed in a scalar memory bank and a larger convolution matrix was placed in a vector bank. Aimed at the problem that the data in the matrix convolution is hard to reuse, a dynamic shuffling pattern with different dynamic configurable parameters based on the moving steps of the convolution kernel was proposed, by carrying out different shift operations on the convolution matrix elements, the multiplexing rate of convolution matrix data was greatly improved. Aimed at the problem that two-dimensional matrix convolution is difficult to multi-core parallelism due to the existence of data correlation, a multi-core parallel scheme with convolution matrix sharing and convolution kernel matrix multi-core exclusive was proposed. Two computing methods of convolution kernel size unchanged, convolution matrix size changed and convolution matrix size unchanged and convolution kernel size changed were designed, a performance comparison and an analysis were carried out in mainstream CPU, GPU, TI6678 and FT-matrix2000. The final experimental results show that compared with the multi-core, the CPU can be accelerated up to 238 times, compared with TI6678, the speed  can be accelerated 21 times, and compared with the highperformance GPU, the speed can accelerate 663 805 times.]]></description>
<pubDate>2018/7/11 12:40:20</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[ZHANG Junyang and GUO Yang]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>ZHANG Junyang and GUO Yang</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201803011]]></guid><cfi:id>129</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Analyses on crack propagation of linear explosive separation system based on extended finite element method]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201803021]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In order to improve the safety of linear explosive separation system, the dynamic crack propagation and crack arrest mechanism during the detonation wave propagation of linear explosive separation device were investigated on the basis of the extended finite element method and by creating 2D and 3D models. The results show that the crack propagation path is independent of the initial angle of preset crack. Without considering the loading sequence, the main directions of crack propagation are radial direction and circumferential direction for 2D and 3D models respectively. Once the loading sequence is taken into account, due to the combined effect of the stress wave from different regions, the 3D crack propagates circumferentially and axially but it does not influence the region outside the crackarrest slot either. The method used and results obtained in the study can provide a solution for the design of explosive separation devices.]]></description>
<pubDate>2018/7/11 12:40:21</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[ZHANG Liang<sup>1</sup>, SHEN Zhibin<sup>1</sup> and JIANG Chunzhi<sup>2</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>ZHANG Liang<sup>1</sup>, SHEN Zhibin<sup>1</sup> and JIANG Chunzhi<sup>2</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201803021]]></guid><cfi:id>128</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Numerical analysis on the combustion characteristics of splash platelet injector]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201802001]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In order to obtain the influence law of structure parameters on the combustion characteristics, the numerical analysis of gaseous methane and gaseous oxygen GO<sub>2</sub>/GCH<sub>4</sub> single-element splash platelet injector was investigated, and the characteristics of both chamber length and nozzle width of faceplate were studied. The chemical N-S equations were solved for the flow field, and 1-step 9-species chemical dynamic model was used to describe the reaction of methane and oxygen. The results indicate that, the characteristic velocity increases with the increase of characteristic chamber length. Under these design parameters, the corresponding value of chamber characteristic length is about 600 mm. By contrast, when the nozzle width is 0.15 mm, the mole fraction of H<sub>2</sub>O has the biggest difference from the theoretical value; the temperatures of flow field increase at the fastest level when the nozzle width equals to 1.05 mm but increase at the slowest level when the nozzle width equals to 0.45 mm. In short, the nozzle width equals to 0.75 mm, the injector can reach the maximum combustion efficiency and the shortest combustion length compared to other cases.]]></description>
<pubDate>2018/5/11 16:33:56</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[YIN Liang and LIU Weiqiang]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>YIN Liang and LIU Weiqiang</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201802001]]></guid><cfi:id>127</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Optimization design of  new unmanned underwater vehicle hybrid propulsion system based on aluminum-water combustion]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201802002]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The unmanned underwater vehicle hybrid propulsion system exploits the exothermic reaction between aluminum and water which will produce high temperature, pressure steam and hydrogen mixture that can be used to drive turbine to generate power. The research shows that this system has high energy density. Three new system configurations corresponding to different working cycles were investigated respectively, and their performance parameters in terms of net power, energy density and global efficiency were discussed. The results of the simulation show that the reaction between the direct return of high temperature steam and the aluminum enhances the temperature of steam, and the system′s performance is reduced. An evaporator component and a solid heat exchanger are added into system in order to make full use of the solid product heat, and so the system performance is improved. The addition of double combustion chamber and wall cooling structure avoid the design of the high temperature compressor component on one hand, and solve the thermal protection of the combustion chamber on the other hand, which brings the improvement of the system performance. The results can provide useful information for the overall design of the unmanned underwater vehicle hybrid propulsion system.]]></description>
<pubDate>2018/5/11 0:00:00</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[CHEN Xianhe, XIA Zhixun, HUANG Liya, NA Xudong and WANG Dequan]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>CHEN Xianhe, XIA Zhixun, HUANG Liya, NA Xudong and WANG Dequan</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201802002]]></guid><cfi:id>126</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Studies of aerodynamic interference characteristics for external store separation]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201802003]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Taking the classic wing pylon finned store model for example, the overset grid system and CFD (computational fluid dynamics) technology were utilized to study the aerodynamic interference characteristics of the external store separation from two aspects:the interference condition simplification and the analysis of factors influencing aerodynamic interference characteristics. The predicted results of missile separation trajectory parameters and aerodynamic interference coefficients coincide well with the CTS(captive trajectory system) results, which indicates that the proposed computing method can effectively predict the separation trajectory and complex aerodynamic interference between the missile and aircraft. Based on the results of CFD numerical simulations, the missile aerodynamic interference law of separation can be obtained for different working conditions of mach number, wing angle of attack, missile angle of attack and so on. Furthermore, the incremental coefficient method with first-order heterodyne processing is also obtained to give aerodynamic interference data for the defect working condition. The proposed method can be utilized to predict the separation trajectory and to design the aerodynamic interference characteristics between the missile and aircraft, thus producing great values in practical engineering applications. ]]></description>
<pubDate>2018/5/11 16:33:56</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[FAN Jingjing<sup>1</sup>, ZHANG Hairui<sup>1</sup>, GUAN Fei<sup>1,2</sup> and ZHAO Changjian<sup>1,2</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>FAN Jingjing<sup>1</sup>, ZHANG Hairui<sup>1</sup>, GUAN Fei<sup>1,2</sup> and ZHAO Changjian<sup>1,2</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201802003]]></guid><cfi:id>125</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Nonsingular finite-time guidance law with missile dynamic]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201802004]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In order to realize intercept angle constraint and finite-time convergence when a missile intercepts a maneuvering target, a guidance model was proposed on the basis of the first-order missile dynamics. By regarding the target acceleration as unknown bounded external disturbance, and by applying the dynamic surface of nonlinear backstepping theory, a nonsingular sliding mode guidance law with missile dynamic was designed. Based on the Lyapunov stability theory, it was proved that the states of guidance system asymptotically converged to zero. Simulations on intercepting targets with constant maneuvering of low attitude and high velocity were made. Simulation results indicate that the designed guidance law can effectively reduce the influence caused by the missile dynamic delay, and the miss distance and the intercept angle error are small; by comparison with the optimal guidance law with missile dynamic and intercept angle constraint, the designed guidance law has higher guidance accuracy. ]]></description>
<pubDate>2018/5/11 16:33:56</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[WANG Chaolun, SONG Baohua and CHANG Chao]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>WANG Chaolun, SONG Baohua and CHANG Chao</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201802004]]></guid><cfi:id>124</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Analytical expression of error propagation along powered phase trajectory of missile by disturbing gravity]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201802005]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Regarding the influence to the inertial navigation system of missile by disturbing gravity was focused, a polynomial fitting method was used to express disturbing gravity along the trajectory, and an analytical expression for calculating the deviation from the nominal value without considering disturbing gravity was deduced based on the linear system theory and the perturbation theory. Moreover, the coupling property between disturbing gravity and apparent acceleration was considered. The apparent acceleration deviation caused by disturbing gravity was regarded as an additional term of disturbing gravity, and was corrected by iterative method. The simulation results show that the error of disturbing gravity fitting method is less than 3×10<sup>-7</sup>m/s<sup>2</sup>, and the residual error of the analytical formula considering the compensation of the apparent acceleration deviation is about 1/3 of the original method, and the computation time is only 1/10 of the numerical integration method.]]></description>
<pubDate>2018/5/11 16:33:56</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[WANG Lei, ZHENG Wei and ZHOU Xiang]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>WANG Lei, ZHENG Wei and ZHOU Xiang</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201802005]]></guid><cfi:id>123</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Analysis of  the skirt bonding properties of solid rocket motor composite case]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201802006]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The skirt bonding properties of the composite case was analyzed by using the numerical method. The finite element model of the filament wound case was established. The contact of the skirt bonding interface was defined with the cohesive zone model. The damage failure criterion was employed and the debonding of the interface was simulated to predict the ultimate load of the skirt structure. Moreover, the distributions of the axial strain and the hoop strain on the case and the shear stress in the interface were investigated. The effects of the elastic modulus and the bonding length on the ultimate tensile load were studied. Numerical example shows that the results have a good agreement with the experimental data, which can provide validity for the present method. The proposed method can be applied to the optimal design of the skirt structure.]]></description>
<pubDate>2018/5/11 16:33:56</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LI Yongfeng<sup>1,2</sup>, ZHANG Fu<sup>2</sup>, SHEN Zhibin<sup>1</sup> and LI Haiyang<sup>1</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LI Yongfeng<sup>1,2</sup>, ZHANG Fu<sup>2</sup>, SHEN Zhibin<sup>1</sup> and LI Haiyang<sup>1</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201802006]]></guid><cfi:id>122</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Buffer allocation algorithm for SpaceWire network in hotspot communication mode]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201802007]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[According to the working characteristics of SpaceWire network in hotspot communication mode, the buffer allocation algorithm was studied. The definition of uniform communication mode and hotspot communication mode were given; the calculation method of full-load probability and the average delay of nodes in the network were deduced, and the key communication nodes in the network were calculated; the buffer allocation algorithm for SpaceWire network was derived. Then, the SpaceWire communication model was established by using the Opnet network simulation platform, and the key performance indexes of the different communication modes were simulated before and after adopting the buffer optimization strategy. The study results show that, in the hotspot communication mode, the buffer allocation algorithm reduces the average delay of the network system under the same total resource. The performance of the SpaceWire network is optimized.]]></description>
<pubDate>2018/5/11 16:33:56</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[GONG Quanming<sup>1,2,3</sup>, YAN Mengting<sup>1,2</sup>, JIANG Xiujie<sup>1,2,3</sup> and AN Junshe<sup>1,2,3</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>GONG Quanming<sup>1,2,3</sup>, YAN Mengting<sup>1,2</sup>, JIANG Xiujie<sup>1,2,3</sup> and AN Junshe<sup>1,2,3</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201802007]]></guid><cfi:id>121</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Environmental parameter online identification and its application in gliding guidance]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201802008]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[A numerical predictor corrector guidance with environmental parameter online identification was proposed for boosting glide missile. Comprehensive environment parameter was introduced in gliding phase concerning both atmospheric density and aerodynamic parameter influence. Extend Kalman filter was used to identify the comprehensive parameter online. Based on identification results, gradual fading-memory recursion least square method was used to build identification model of environment parameter. And the model was gradually revised based on the updated identification. Longitudinal and lateral guidance laws were designed. Drop point was estimated based on the identification model to limit the influence of environmental disturbance. The guidance simulations were carried out with atmosphere density and aerodynamic disturbance. The results demonstrate the identification model can predict the environment parameters accurately and the guidance method has enough robustness to environmental disturbance.]]></description>
<pubDate>2018/5/11 16:33:56</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[JIANG Zhenyu<sup>1</sup>, SUN Leyuan<sup>2</sup>, WANG Jinlin<sup>3</sup>, HUANG Zhenxin<sup>1</sup> and ZHAO Lei<sup>1</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>JIANG Zhenyu<sup>1</sup>, SUN Leyuan<sup>2</sup>, WANG Jinlin<sup>3</sup>, HUANG Zhenxin<sup>1</sup> and ZHAO Lei<sup>1</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201802008]]></guid><cfi:id>120</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Dynamic response analysis of the hyper-static strap-on boosters based on the bi-linear connection model]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201802009]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In order to increase the connect reliability between the core stage and the boosters of the launch vehicle, the boosters with large fineness ratio can use hyper-static strap-on style. However, it may increase the analysis difficulty of the dynamic characters. Therefore, the dynamic model of booster with hyper-static strap-on style was established, and the bi-linear stiffness spring was employed to simulate the strap-on equipment. The dynamic response of the booster by the radial impulsion will be researched. The responses, including generalized displacements, frequency and the internal force will be compared with the static strapon style. Research results can provide reference and theoretical support for the engineering application.]]></description>
<pubDate>2018/5/11 16:33:57</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[FENG Shaowei<sup>1</sup>, WANG Yue<sup>2</sup>, CHEN Xiaofei<sup>1</sup>, GUO Fengming<sup>1</sup> and LENG Yue<sup>1</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>FENG Shaowei<sup>1</sup>, WANG Yue<sup>2</sup>, CHEN Xiaofei<sup>1</sup>, GUO Fengming<sup>1</sup> and LENG Yue<sup>1</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201802009]]></guid><cfi:id>119</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Modeling and performance analysis of deeply precooled combined cycle engine in the air-breathing mode]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201801001]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The modeling and performance calculation for the deeply precooled combined cycle engine—SABRE(synergistic air-breathing rocket engine) were carried out. A steady componentlevel model of the engine was constructed. The rule of performance variation of the engine in the air-breathing mode along the flight trajectory was obtained, and the altitude-velocity characteristic of the engine was studied. The model is reliable with thrust error less than 6%, and it can be used to calculate performance of SABRE under the air-breathing mode. It is indicated that the SABRE is characterized by both large thrust as rocket engines and high specific impulse as aircraft engines, and its specific impulse is between 21 300~27 380 m/s; along with the increase of altitude and velocity, the thrust and specific impulse of SABRE increase first and then decrease. By decreasing the inlet airstream temperature with precooler, the range of height and velocity of SABRE can be enlarged to 25 km and 5Ma, which is required by hypersonic flight; the lower limitation of velocity is decided by the maximum mass flow rate of compressor, and the higher limitation is decided by the operation rule of helium loop.]]></description>
<pubDate>2018/3/23 11:05:18</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[ZHANG Jianqiang<sup>1,2</sup>, WANG Zhenguo<sup>1,2</sup> and LI Qinglian<sup>2</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>ZHANG Jianqiang<sup>1,2</sup>, WANG Zhenguo<sup>1,2</sup> and LI Qinglian<sup>2</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201801001]]></guid><cfi:id>118</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Improvement of elasticity-based dynamic grid methodbased on mesh quality feedback]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201801002]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Dynamic grid deformation method with higher robustness is critical for unsteady flow problems which include moving boundaries. Two of rational and effective mesh quality parameters were introduced, namely Patrick parameters and Baker parameters. Then, a modified dynamic grid method was presented, which can optimize mesh quality on term of mesh quality feedback. Combined with large-pitching of 2D NACA0012 airfoil and 3D ONERA M6 wing, the difference between modified method and classical method was fully analyzed. Modified method has obvious advantage in mesh quality, and at the largest moving degree, it can significantly enhance the robustness of grid mainly through perfecting the worse element. Finally, the modified method was applied to simulate the pitching motion of NACA0012 airfoil and ONERA M6 wing, and  the calculations were compared with the experimental values and literature. Result shows that the modified method can improve stronger robustness, therefore it can provide better support for unsteady flow problems.]]></description>
<pubDate>2018/3/23 11:05:18</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[ZHANG Bin, YANG Tao, FENG Zhiwei, ZHANG Qingbin and GE Jianquan]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>ZHANG Bin, YANG Tao, FENG Zhiwei, ZHANG Qingbin and GE Jianquan</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201801002]]></guid><cfi:id>117</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Sliding mode fault tolerant attitude control for satellitebased on iterative learning observer]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201801003]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[A novel fault tolerant attitude control scheme was proposed based on ILO (iterative learning observer) for satellite with unknown reaction wheel faults, uncertainties and unknown external disturbances. More specially, an iterative learning observer was derived to estimate reaction wheel faults and uncertainties accurately with less online computing power. Secondly, based on the estimated information, a sliding mode controller was derived to achieve the attitude stability of satellite rapidly with unknown external disturbances and reaction wheel faults. Furthermore, the stability of the ILO and  the controller were approved by using the Lyapunov stability theory. Finally, simulations were carried out for satellite with unknown reaction wheel faults, uncertainties and disturbances. Results demonstrate that the proposed control scheme is more effectively and displays more feasibility by comparing with other fault tolerant control approach.]]></description>
<pubDate>2018/3/23 0:00:00</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[ZHANG Zhongzheng, YE Dong and SUN Zhaowei]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>ZHANG Zhongzheng, YE Dong and SUN Zhaowei</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201801003]]></guid><cfi:id>116</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Fault-tolerant algorithm and information management for redundant strapdown inertial navigation system]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201801005]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[A new algorithm based on intersection fault-tolerant fusion and unscented Kalman filter was proposed for fault diagnosis, isolation and reconstruction of skew redundant strapdown inertial navigation system. Considering the error coefficients of gyros, a unified model was built for redundancy configuration. A single point of failure can be isolated rapidly with the intersection fusion model, and an unscented Kalman filter was used for the error coefficients of isolated gyros, which can determine soft failure caused by error coefficients′ change. The simulation with configuration of 5 gyros shows the validity of algorithm under 2 soft failure caused by error coefficients′ change.]]></description>
<pubDate>2018/3/23 11:05:19</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[ZHOU Weizheng<sup>1</sup>, LI Xuefeng<sup>1</sup> and ZHAO Saijun<sup>2</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>ZHOU Weizheng<sup>1</sup>, LI Xuefeng<sup>1</sup> and ZHAO Saijun<sup>2</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201801005]]></guid><cfi:id>115</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Flexural and free vibrational analysis of tapered partially steel-concrete composite beams using the weak form quadrature element method]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201801007]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Quadrature element formulations for tapered partially steel-concrete composite beams were established based on the Newmark model and the plane stress model respectively. Deformation of tapered partially composite beams under distributed loading and free vibrational problems with two representative boundary conditions were examined. It is shown that for slender and slightly tapered composite beams common in engineering the proposed 1D quadrature element model is effective enough for flexural and fundamental frequency analysis. Moreover, the 2D quadrature element model is capable of providing better results when needed.]]></description>
<pubDate>2018/3/23 11:05:19</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[SHEN Zhiqiang<sup>1</sup>, XIA Jun<sup>1,2</sup>, WU Kegang<sup>1</sup>, HU Qigao<sup>1</sup> and CHENG Pan<sup>1</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>SHEN Zhiqiang<sup>1</sup>, XIA Jun<sup>1,2</sup>, WU Kegang<sup>1</sup>, HU Qigao<sup>1</sup> and CHENG Pan<sup>1</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201801007]]></guid><cfi:id>114</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Advances and key scientific problems in deployable sunshield structures]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201801009]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[A deployable sunshield generally consists of layers flexible, wrinklefree multilayer membranes with high precision, deployable booms and its control equipments.  The deployable booms can orderly unfold the multilayer membrane after on-orbit to realize its light control and heat control performance, and it can effectively improve the protection on the aerospace systems. The state-of-the-art of domestic and international deployable sunshield structures were classified and summarized according to their deployable methods of one dimensional axial, two-dimensional plane and three-dimensional circumferential way, as well as the comparison to different structural design and the membrane materials. Some key scientific problems for the sunshields were presented in stray light suppression, folding and deployable deformation mechanism, more field coupling on membranes under the extreme environment, low temperature thermal control, and other aspects of solar pressure moment and computing methods. In addition, some recommendations were also given for the sunshield progress and research in China.]]></description>
<pubDate>2018/3/23 11:05:19</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[WEI Jianzheng<sup>1</sup>, LIN Qiuhong<sup>2</sup>, LIN Guochang<sup>1</sup> and TAN Huifeng<sup>1</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>WEI Jianzheng<sup>1</sup>, LIN Qiuhong<sup>2</sup>, LIN Guochang<sup>1</sup> and TAN Huifeng<sup>1</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201801009]]></guid><cfi:id>113</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Analysis of CODE′s new solar radiation pressure model on precise orbit determination for mixed-type BeiDou constellation]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201801013]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The performance of CODE′s new solar radiation pressure model, the EECOM (extended empirical CODE orbit model), was analyzed on precise orbit determination for mixed-type BeiDou constellation. This study is based on the NUDTTK software, which is a satellite orbit determination toolkit. The validation of satellite laser ranging reveals that the EECOM can improve orbital accuracy of geostationary earth orbit satellites by 17.4% and 35.1%, compared with traditional CODE′s ECOM-9 and ECOM-5 models, respectively. As to the inclined geosynchronous earth orbit and the medium earth orbit satellites, the ECOM-5 model performs better than EECOM as well as ECOM-9 model. It means that CODE′s new solar radiation pressure model is not able to improve the orbital accuracy of the inclined geosynchronous earth orbit and the medium earth orbit satellites. External orbit validation by IGS data analysis centers of GFZ, WHU and CODE indicates that the accuracy of our current BeiDou precision orbit is 1~4 m for geostationary earth orbit satellites, 25~30 cm for inclined geosynchronous earth orbit satellites and 10~20 cm for medium earth orbit satellites, respectively.]]></description>
<pubDate>2018/3/23 11:05:19</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[JU Bing<sup>1，2</sup>, CHANG Xiao<sup>1</sup>, GU Defeng<sup>1</sup>, DUAN Xiaojun<sup>1</sup> and WANG Zhengming<sup>1</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>JU Bing<sup>1，2</sup>, CHANG Xiao<sup>1</sup>, GU Defeng<sup>1</sup>, DUAN Xiaojun<sup>1</sup> and WANG Zhengming<sup>1</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201801013]]></guid><cfi:id>112</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Active vibration control with optimal actuator for flexible structures]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201801025]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Flexible structures are widespreadly applied in fields of aerospace. In order to obtain the best dynamic performance of the structures, the optimal locations of actuator and sensor become a key problem in active vibration control. The new proposed optimization criteria based on finite element dynamic equation ensuring good controllability or observability of the structures and considering the remaining modes effect were derived. Non-linear integer programming genetic algorithm was utilized to find the optimal positions of actuator and sensor. A cantilever plate was simulated by using state-feedback linear quadratic regulation controller to validate the vibration suppression effects. The comparison results of numerical simulation demonstrate the advantages of the proposed method.]]></description>
<pubDate>2018/3/23 11:05:20</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[GAO Weijin, WANG Liang and LIU Yongguang]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>GAO Weijin, WANG Liang and LIU Yongguang</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201801025]]></guid><cfi:id>111</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Construction of intelligent capability on spacecrafts]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201905001]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In order to apply intelligent technology to enhance the intelligent capability of spacecrafts, the intelligent level from deployment viewpoint was given. The start point of qualitative levels is automatic, autonomous and autonomic. It includes such capabilities as execution,  self-learning, system self-management, mission self-management, thinking and planning from the bottom up. The behavior degrees are bottom-reactive, middle-program and high-thinking. According to the above capability levels, a 5-stage model and an intelligent architecture named “people shape architecture” were proposed. A human-body shape architecture was formulated with two supporting technologies (plug and play, autonomic control) to construct intelligent body on higher level. In this model, based on spacecraft onboard interface services and ESA packet utilization standard services, management information base and electronic data sheet were used for dataoriented design. Corresponding to the intelligent level, appropriate supporting capability of ground system was discussed. People shape architecture has some features including layering, modeling, unification for constructing of intelligent bottom-up architecture, and is open to use intelligent technology in higher layers.]]></description>
<pubDate>2019/9/30 15:58:00</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LYU Liangqing<sup>1,2</sup>, WU Di<sup>1,2</sup> and AN Junshe<sup>1</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LYU Liangqing<sup>1,2</sup>, WU Di<sup>1,2</sup> and AN Junshe<sup>1</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201905001]]></guid><cfi:id>110</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Conceptual analysis of  rocket dual combustion ramjet combined-cycle engine]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201905002]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Increasing attention has been paid to near space plane in recent years. In the present study, a multi-module RDCRC (rocket dual combustion ramjet combinedcycle) engine was proposed to power the near space plane and its performance was analyzed. The plane was designed to drop at about Mach 0.8 and 10 km above sea level. Under the gravity and the combination thrust of the engine, the plane accelerates to about Mach 2 at 5~8 km above sea level. Then, it climbs up and accelerates the near space under the ejector-ramjet mode or DCR ramjet mode. The ejector-ramjet mode provides higher acceleration with less efficiency, while the DCR ramjet mode provides more efficiency and lower acceleration, thus the mode can be transformed according to the actual situation. Finally, the plane climbs up to about 26 km above sea level, accelerates to Mach 6, and starts to cruise in DCR scramjet mode. A trajectory optimization was carried out for air launch and surface launch, and the obtained results show that the air launch can save about 37% propellant with Mach 6 and 26 km above sea level, and there lies a negative optimal initial flight angle that leads to an optimum ratio between the residual mass and the initial mass.]]></description>
<pubDate>2019/9/30 15:58:00</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[WU Jiping<sup>1,2</sup>, TAN Jianguo<sup>1,2</sup>, CHEN Jian<sup>1,2</sup> and ZHANG Zihao<sup>1,2</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>WU Jiping<sup>1,2</sup>, TAN Jianguo<sup>1,2</sup>, CHEN Jian<sup>1,2</sup> and ZHANG Zihao<sup>1,2</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201905002]]></guid><cfi:id>109</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Lowobservable glide trajectory optimization method for hypersonic vehicle]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201905003]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In order to further improve the penetration ability of hypersonic vehicle, the low-observable glide trajectory optimization method for hypersonic vehicle was proposed. The radar cross section of 180°×360° direction of the aircraft was considered. The Gaussian filtering method was used to smoothing the original data, which was characterized by many spikes. This can improve the convergence of optimization problems without changing the trend of the original data. In order to enable the RCS (radar cross section) data to have strong fidelity, the cubic spline interpolation method was used to call the discrete data. The modelling of the low detectable glide trajectory optimization problem of hypersonic vehicle was completed. Setting the radar detection probability as the objective function, the hp adaptive Radau pseudo-spectral method was used to solve the problem. The stepwise calculate strategy was adopted to further improve the optimization efficiency and convergence performance. Simulation results show that when compared with the trajectory who takes the shortest flight time as the goal, the given method can effectively reduce the radar detection probability.]]></description>
<pubDate>2019/9/30 15:58:00</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[HUANG Hao, FENG Zhiwei, GE Jianquan, YANG Tao and XU Qiangqiang]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>HUANG Hao, FENG Zhiwei, GE Jianquan, YANG Tao and XU Qiangqiang</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201905003]]></guid><cfi:id>108</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Adaptive grid fast assignment method for gravity anomaly of skip-gliding trajectory]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201905004]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In order to achieve fast assignment of gravity anomaly for skip-gliding trajectory in hypersonic speed, an adaptive grid assignment model was proposed, and the generalized extension approximation algorithm was optimized based on the inverse distance weighting theory,  the approximation error of the model was analyzed as well. The space of the assignment model was divided at two levels. The first level grid was divided according to the standard ballistic airspace, and the second level adaptive grid was built online according to the actual trajectory of the missile. According to the data of the first level grid nodes, the data of the second level grid nodes were calculated by optimized generalized extension approximation algorithm. Finally, the gravity anomaly value of the actual ballistic points was calculated by interpolation algorithm within the second level grid. The simulation results show that the approximation accuracy of the optimized generalized extension adaptive grid model is higher than that of the general assignment method under the grid with same size. Under the same precision, the maximum grid length of the assignment model is larger than the general assignment method, which can  the number of grid division and the amount of data stored on the missile.For the different gliding direction and gliding distance of the jump gliding trajectory, the drop point deviation corresponding to the gravity anomaly approximation error less than 5 m. On the premise of satisfying the calculation speed, this assignment model improves the accuracy of the traditional assignment method and reduces the amount of storage on the missile, and has a certain value of engineering application.]]></description>
<pubDate>2019/9/30 15:58:00</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[WANG Shunhong, DAI Chenchao, LI Jian and YANG Qisong]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>WANG Shunhong, DAI Chenchao, LI Jian and YANG Qisong</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201905004]]></guid><cfi:id>107</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Experimental investigation on performance of four-strut supersonic ejector]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201905005]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[A four-strut supersonic ejector with two-dimensional nozzle configuration was tested in cold flow, the performance of start and load match properties were analyzed. The experiment results indicate that the static pressure of suction chamber in four-strut supersonic ejector is less than 3 kPa and the pressure of ejector inlet chamber in delay status is 15.9% lower than that in start status. In the aspect of load match property, the four-strut ejector with small entrainment ratio and big pressure ratio has a quite obvious advantage. When the entrainment ratio is 0.04, the corresponding pressure ratio is 11.21; when the entrainment ratio is 0.10, the corresponding pressure ratio is 11.21. Therefore, the multi-strut supersonic ejector with two-dimensional nozzle configuration has good performance of start and load match properties, thus possessing considerable potential value in engineering.]]></description>
<pubDate>2019/9/30 15:58:00</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[YE Wei<sup>1,2</sup>, XU Wanwu<sup>1,2</sup>, LI Ping<sup>1,2</sup>, ZHANG Fuqiang<sup>1,2</sup>, DAI Xuncheng<sup>1,2</sup> and XIAO Li<sup>1,2</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>YE Wei<sup>1,2</sup>, XU Wanwu<sup>1,2</sup>, LI Ping<sup>1,2</sup>, ZHANG Fuqiang<sup>1,2</sup>, DAI Xuncheng<sup>1,2</sup> and XIAO Li<sup>1,2</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201905005]]></guid><cfi:id>106</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Optimization of geometrical parameters of bolted flange by modified response surface method]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201905006]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In consideration of the limitation of TRSM (typical response surface method), a MRSM (modified response surface method) which was based on the inner connection between optimization parameters and appointed response was put forward. Several numerical experiments were conducted, and the  results were compared with the predicted values of both models. The comparative results show that the MRSM′s predicted values are more uniform than TRSM′s and the max error absolute value is smaller than TRSM′s. By using genetic algorithm, the MRSM is optimized whose aim is to minimize the weight of flange and an ideal result is obtained.]]></description>
<pubDate>2019/9/30 15:58:00</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[JIANG Guoqing, CHEN Wanhua and WANG Yuanxing]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>JIANG Guoqing, CHEN Wanhua and WANG Yuanxing</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201905006]]></guid><cfi:id>105</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Electromagnetic launch hypervelocity integrated projectile]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201904001]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Regarded as the launch object of EM (electromagnetic) energy weapon, the hypervelocity ILP (integrated launch projectile) has a lot of scientific problems different from those caused from traditional artillery. The theoretical and experimental results of EM launch ILP at home and aboard in recent years were summarized, and the basic theory and key technologies faced right now were analyzed. In addition, the solutions to these problems are put forward to provide some references to the subsequent research on EM launch ILP.]]></description>
<pubDate>2019/7/18 0:00:00</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[MA Weiming, LU Junyong and LI Xiangping]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>MA Weiming, LU Junyong and LI Xiangping</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201904001]]></guid><cfi:id>104</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Simulation of flight ballistic of electromagnetic launch projectile]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201904004]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The flight ballistic of the EML (electromagnetic launch) projectile was simulated. Based on the establishment of a rigid body six degree of freedom flight external ballistic model, the time-frequency analysis and eddy current analysis method were adopted to establish the EMdynamic coupling model for the analysis of muzzle disturbance caused by the interior vibration, and the dynamic grid technology was used to establish the EM-aerodynamic coupling model for the analysis of aerodynamic disturbance brought by sabot discard. Thereby, the flight trajectory model of EML projectile was obtained. Taking the IAT-HVP designed by the advanced technology research institute of University of Texas as an example, the influence of the muzzle disturbance on the velocity and aerodynamic characteristics of the projectile was simulated and analyzed when the projectile leaves the muzzle at 1117 m/s with 0° angle of fire, and the 200 m exterior trajectory of the projectile was obtained. Simulation results show that 24% deviation of the drop point relative to idea ballistic are caused by the disturbance of the integrated projectile in the muzzle, in which the maximum is caused by the muzzle vibration, and secondly the sabot discard.]]></description>
<pubDate>2019/7/18 15:28:48</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LI Xiangping, LU Junyong, FENG Junhong, LI Kai and DU Peipei]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LI Xiangping, LU Junyong, FENG Junhong, LI Kai and DU Peipei</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201904004]]></guid><cfi:id>103</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Primary breakup process of liquid jet in supersonic crossflow]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201904011]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The transient image of the liquid jet in supersonic crossflow was obtained by microphotography method and the spatial resolution was 1.57 μm/pixel. The evolution of the surface wave was phenomenologically analyzed. The 3D flow field and liquid column structure were numerically investigated through volume of fluid method and the gasliquid interaction was discussed accordingly. The primary breakup of liquid jet experiences two physical processes: the column breakup and the surface breakup. The column breakup is dominated by RT instability from gasliquid acceleration while the surface breakup is dominated by KH instability from gasliquid shearing. The oscillation of the local pressure around the jet surface should be the main mechanism of the generation and evolution of the surface wave. The recirculation flow generates leeward the jet column since the interaction of the supersonic flow and the continuous liquid column. Therefore, the spray near the bottom wall contains two portions: the shearing spray from the surface breakup and the transporting spray through the recirculation flow.]]></description>
<pubDate>2019/7/18 0:00:00</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LI Chun<sup>1,2</sup>, SHEN Chibing<sup>1,2</sup>, LI Qinglian<sup>1,2</sup> and ZHU Yuanhao<sup>1,2</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LI Chun<sup>1,2</sup>, SHEN Chibing<sup>1,2</sup>, LI Qinglian<sup>1,2</sup> and ZHU Yuanhao<sup>1,2</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201904011]]></guid><cfi:id>102</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Fault simulation of ducted rocket based on system configuration switch method]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201904012]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In order to comprehensively verify the fault detection algorithm in the ducted rocket rapidly, a simulation platform based on system configuration switch method was built, which can simulate various fault mode for ducted rocket. Based on the simulation platform, the ducted rocket ignite fault model, pressure sensor fault model, device interface model and fault detection algorithm model which have a same interface and system configuration with the aircraft engine controller, etc. were built. Compared with the fault detect result of mathematical model and engine control system under a same fault mode, the fault detection algorithm in the engine control system can be verified rapidly. Taking the fault simulation of nozzleless booster ignition as an example, the modeling, the test, the verification, and the process of analysis were narrated. In addition, it is also applicable to the fault simulation and verification of the shutdown of nozzleless booster, the open of air inlet cover, the ignition of gas generator, and fault tolerant control of gas flow, which has strong universality, and can greatly reduce the time cost on system development and verification, and it has a strong applied value.]]></description>
<pubDate>2019/7/18 0:00:00</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[WANG An<sup>1</sup>, ZENG Qinghua<sup>2</sup> and ZHOU Yuchen<sup>1</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>WANG An<sup>1</sup>, ZENG Qinghua<sup>2</sup> and ZHOU Yuchen<sup>1</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201904012]]></guid><cfi:id>101</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Design of highly reliable SpaceWire routers based on FPGA]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201904013]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[A system design method for SpaceWire router based on SRAM FPGA(fieldprogrammable gate array) was proposed to improve its reliability and availability. The router was hardened by system level triple modular redundancy; and the dynamic partial scrubbing technique based on bitstream relocation was adopted to repair the faulty module in case of soft errors. Meanwhile, a real-time state synchronization approach based on present input and healthy state was introduced to synchronize the repaired module′s state with the other modules′ after scrubbing. Hence the router is capable of error masking and selfhealing. The proposed design method was implemented and verified on the Xilinx Virtex-5 FPGA develop kit ML507. Experimental results show that the reliability and availability of the router are increased significantly. And the router′s real-time performance is satisfactory, such that it can offer normal service during the entire work process, without any interruption or delay in system functionality. Meanwhile, the amount of memory required is reduced to one-third of the original amount as a result of adopting the bitstream relocation technique, and the failure probability of the original bitstream is also greatly reduced.]]></description>
<pubDate>2019/7/18 0:00:00</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[YAO Rui<sup>1</sup>, WANG Meiqun<sup>1</sup>, WU Jun<sup>2</sup>, HU Jie<sup>1</sup> and LI Mingli<sup>1</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>YAO Rui<sup>1</sup>, WANG Meiqun<sup>1</sup>, WU Jun<sup>2</sup>, HU Jie<sup>1</sup> and LI Mingli<sup>1</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201904013]]></guid><cfi:id>100</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Influence of airborne trajectory of wake simulator rocket on formation area of simulated wake]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201904014]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In order to study the effects of the airborne ballistic characteristics of wake simulation rockets on the simulated wake area, the exterior ballistic model of the rocket projectile, the space motion differential equation of the resistance plate and the engine, the force model of the connecting rope were established. The differential equations of space motion in the whole process of uncontrolled flight, air steering, air separation and unfolding of the detonating cable were obtained. The whole trajectory of the tail-flow-simulated-rocket was simulated and analyzed. The effect of different initial firing elements on the air trajectory of the detonating cable was emphatically analyzed. The influence of initial launch angle, the number of pulse tubes, the ignition time and the rocket separation time on simulated wake generation region were investigated. The simulation results show that the range and maximum shot height of the rocket projectile are relatively reasonable when the initial launch angle is 15 degrees. The angle of the rocket′s air steering depends on the total impulse of the pulse engine and has nothing to do with the ignition time. The effect of air separation time on the water foaming area of the detonating cord is not obvious. Air steering and separation should be completed as soon as possible when the steering requirements and the requirements of the foamed area are met.]]></description>
<pubDate>2019/7/18 0:00:00</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[ZHANG Rui<sup>1</sup>, YUAN Zhiyong<sup>1</sup>, LIU Zhongle<sup>1</sup> and ZHANG Chong<sup>2</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>ZHANG Rui<sup>1</sup>, YUAN Zhiyong<sup>1</sup>, LIU Zhongle<sup>1</sup> and ZHANG Chong<sup>2</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201904014]]></guid><cfi:id>99</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Propeller noise study in nonuniform turbulence]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201904016]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Based on the correlation approach in uniform turbulence, the formula of propeller broadband noise in non-uniform turbulence was deduced to analyze the unsteady noise problem of propeller. For uniform turbulence, the ten-bladed propeller model was used, and the calculated result was compared with the experiments data, which shows a good agreement. For non-uniform turbulence, the results show that the degree of non-uniformity have no effect on the position of the peak in sound spectrum which depends on the blade frequency, but it can change the degree of hump in blade frequency. Finally the effects of skew angle to propeller noise in uniform and non-uniform turbulence were studied，and the results show the skew angle of blade can reduce the noise spectrum of propeller in turbulence.]]></description>
<pubDate>2019/7/18 15:28:49</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[PU Jijun, ZHOU Qidou and LYU Xiaojun]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>PU Jijun, ZHOU Qidou and LYU Xiaojun</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201904016]]></guid><cfi:id>98</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Missile cooperative attacking guidance law with field-of-view limit]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201904017]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In order to achieve cooperative attack of multiple missiles, the impact time and impact angle control guidance-law with field-of-view limit was proposed. A new impact time and impact angle control guidance-law was derived by adding two biases to proportional navigation, and the stability is analyzed by the Lyapunov theory. The guidance process with seeker field-of-view limit was designed by dividing angle control bias term into three stages for the reason that the seeker look angle may overstep the field-of-view and lose the target. Simulation results show that the seeker look angle is limited within the view field of the seeker and multiple missiles at different positions attack the target at a specific angle at the same time, achieving the cooperative attack effect under the designed guidance-law.]]></description>
<pubDate>2019/7/18 15:28:49</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[ZHAO Jiufen, SHI Shaokun, YOU Hao and YANG Qisong]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>ZHAO Jiufen, SHI Shaokun, YOU Hao and YANG Qisong</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201904017]]></guid><cfi:id>97</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Optimization and selection of BDS triple-frequency combination observations based on a weighted fuzzy C-means algorithm]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201903015]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Based on the error analysis of the BDS(BeiDou navigation satellite system) triple-frequency carrier phase observations, the screening criteria for the optimal carrier phase linear combination coefficients was determined. For high-dimensional multifrequency mixed data sets, a weighted fuzzy C-means clustering algorithm was used to assign partial BDS triple-frequency carrier phase observations obtained by traditional ergodic search methods through assigning different weight values to different clusters on the same dimension. The combined observations were optimized for classification and selection, which effectively solved the problem of low efficiency of the traditional GNSS(global navigation satellite system) carrier phase observations selection method, and provided an idea for the optimal selection of the combined observation value coefficients of multi-system multi-frequency data. Finally, the classification results were analyzed, and the applicable range of all kinds of combined observations was determined. The integer ambiguity of the optimal combination is calculated by using the geometric-freed CIR(cascading integer resolution) algorithm and the measured data, and the feasibility and reliability of the method are proved.]]></description>
<pubDate>2019/6/13 15:22:19</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[MENG Fanjun<sup>1</sup>, LI Shujun<sup>1</sup>, PAN Zongpeng<sup>2</sup>, SUN Yicheng<sup>1</sup> and LI Zhongpan<sup>2</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>MENG Fanjun<sup>1</sup>, LI Shujun<sup>1</sup>, PAN Zongpeng<sup>2</sup>, SUN Yicheng<sup>1</sup> and LI Zhongpan<sup>2</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201903015]]></guid><cfi:id>96</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Design of communication architecture for end-to-end IP tunnel protocol oriented space utilization payload]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201903016]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In ground operation and control subnet and payload information network using IPsec, GRE or RFC2003 three IP tunnel protocol, through the platform information network and the telemetry, tracking, and command network, the user data encapsulated into IP tunnel protocol can be routed in communication link between the spacecraft and the ground so as to support the payload and the ground transport flexible end-to-end communication between two control terminals. The information management architecture of world integration was designed to support IP communication, the setting of router and IP address allocation were given，and the communication efficiency and timeliness of three IP tunnel protocols were calculated and analyzed. The analysis result shows that the IP tunnel protocol is of revolutionary significance to change the traditional ground operation and control mode and improve the efficiency of operation and control.]]></description>
<pubDate>2019/6/13 15:22:19</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[QIU Aihua, ZHANG Tao, QIAO Kuangyi and GU Yidong]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>QIU Aihua, ZHANG Tao, QIAO Kuangyi and GU Yidong</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201903016]]></guid><cfi:id>95</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Real-time image processing acceleration strategy in foggy weather condition]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201903017]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In order to simulate forward looking infrared seeker′s matching guidance process, an acceleration strategy aiming at the contrast-limit adaptive histogram equalization and the normalization cross correlation algorithms was researched to realize realtime target tracking judgment. The real-time processing acceleration strategy of foggy images based on CUDA(compute unified device architecture) was proposed. The final real-time graph preprocessing acceleration schema implements two main design parameters′ optimization, including blocksize and blockgrid. Experimations show that using CUDA acceleration schema, the work efficiency is 5~20 times faster than the original algorithm. The proposed acceleration schema can satisfy the realtime target tracking judgment and can provide references to researchers devoted to the related work.]]></description>
<pubDate>2019/6/13 15:22:19</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[CUI Wen<sup>1</sup>, LI Qiang<sup>1</sup>, LIU Xiaochun<sup>2</sup> and LI You<sup>3</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>CUI Wen<sup>1</sup>, LI Qiang<sup>1</sup>, LIU Xiaochun<sup>2</sup> and LI You<sup>3</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201903017]]></guid><cfi:id>94</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Aviation aluminum crack propagation behavior in multiple service environment]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201903018]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The aviation aluminum alloy accelerated corrosion test spectrum was established according to the environment spectrum conducting process after collecting the airports environment data. Based on the accelerated corrosion test spectrum, aluminum alloy LD2CS pre-corroded fatigue test was carried out. Test data were analyzed statistically and the three main corrosion damage characterization factors, namely maximum pit depth, maximum pit width and pit surface rate, were sifted out by using MIV (mean impact value) method. Then the corrosion damage composite indictor α was computed by applying the normalization non-dimension and the weighted average methods. By comparing the characteristics of fatigue precrack propagation behaviors at different corrosion damage levels, the corrosion acceleration coefficient Ω(α) was defined to correct the classical fatigue crack growth formula. The validity of Ω(α)expression was verified by employing test data corroding the 18th to 20th equivelent years and the relative errors were all below 10%. It demonstrates that the corrected fatigue crack growth function in flight transfer environment is appropriate for reflecting the corrosion damage acceleration effect on crack propagation, which proposing new ideas for aviation aluminum alloy damage tolerance design.]]></description>
<pubDate>2019/6/13 15:22:19</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[YAN Guangyao, LIU Zhiguo, MU Zhitao and LI Xudong]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>YAN Guangyao, LIU Zhiguo, MU Zhitao and LI Xudong</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201903018]]></guid><cfi:id>93</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Influence of over-under TBCC on the performance of hypersonic aircraft]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201902001]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Two kinds of combined-cycle propulsions were studied to meet the requirement of a hypersonic vehicle that cruises at Mach number 6. One consists of T/RJ/DMSJ (turbine engine, ramjet and dual mode scramjet), while the other consists of PCT/RJ/DMSJ (pre-cooled turbine engine, ramjet and dual mode scramjet). The ranges and the flying time of the hypersonic vehicle which uses T/RJ/DMSJ and PCT/RJ/DMSJ were obtained under thrust weight ratio of 0.8 and 1.0 with a given mission. The performances of two operating mode of PCT/RJ/DMSJ were compared. Results show that the range and the flying time of the two combined-cycle propulsions are almost close. The range of PCT/RJ/DMSJ is 3.6% higher than T/RJ/DMSJ and the flying time of PCT/RJ/DMSJ is 3.8% more than T/RJ/DMSJ under thrust weight ratio of 0.8. When the thrust weight ratio is 1.0, the range and the flying time of PCT/RJ/DMSJ are 4.6% and 4.8% higher than T/RJ/DMSJ, respectively. Under the lower thrust weight ratio, the fuel consumption of the transonic flying phase is the largest part during the acceleration and climbing process. The fuel consumption of the transonic flying phase decreases as the increase of thrust weight ratio and then more fuel can be used in the hypersonic cruise and the cruise distance increases. The range increases and the flying time decreases as the increase of thrust weight ratio.]]></description>
<pubDate>2019/4/24 14:24:47</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[MA Song<sup>1,2</sup>, LIN Peng<sup>2</sup>, ZUO Linxuan<sup>2</sup>, WANG Xiao<sup>1,2</sup> and TAN Jianguo<sup>1</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>MA Song<sup>1,2</sup>, LIN Peng<sup>2</sup>, ZUO Linxuan<sup>2</sup>, WANG Xiao<sup>1,2</sup> and TAN Jianguo<sup>1</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201902001]]></guid><cfi:id>92</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Centralized payload control method for planetary rover exploration]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201902002]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[To satisfy the requirement for autonomous scientific detection in resource constrained planetary rover exploration mission, a centralized payload control method was proposed. A novel highly integrated hardware architecture was constructed by integrating payload electronics units and traditional payload OBDH (onboard data handling) unit. The software adopted the control method based on the event table and work mode table to control the payload autonomously. Several health management measures were taken to make fault recovery and isolation according to pre-defined rules. The common control part weighs only 3 kg, and consumes 6 W power. The software supports 9 work mode tables running at the same time. Instruction executing time accuracy is better than 40 ms.The method has been applied to China first Mars exploration. Ground test results show that the method is simple, efficient and reliable, and suitable for payload control in planetary rover exploration missions with harsh resource constraints.]]></description>
<pubDate>2019/4/24 14:24:48</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[WANG Lianguo<sup>1,2</sup>, ZHU Yan<sup>1</sup>, MA Miao<sup>1</sup>, RAO Jianing<sup>1</sup>, LIANG Yaoming<sup>1</sup> and WANG Wei<sup>1</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>WANG Lianguo<sup>1,2</sup>, ZHU Yan<sup>1</sup>, MA Miao<sup>1</sup>, RAO Jianing<sup>1</sup>, LIANG Yaoming<sup>1</sup> and WANG Wei<sup>1</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201902002]]></guid><cfi:id>91</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Linear stability analysis of conical liquid film with coaxial annular gas flow]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201902003]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In order to analyze the atomization mechanism of gas liquid swirl injector, a temporal linear stability analysis method was used to investigate the conical liquid film with coaxial annular gas flow. The dispersion equation of a conical liquid film with coaxial annular gas flow was derived and a prediction model was proposed to calculate the parameters needed in solving the dispersion equation. The results show that the film thickness at the injector exit decreases with the increase of pressure drop while the spray cone angle, liquid film velocity and liquid film axial velocity increase with the increase of pressure drop. The sinuous mode disturbance wave dominates the breakup process of conical liquid film with coaxial annular gas flow because the growth rate of sinuous wave is much larger than that of varicose wave. When the gas flow velocity is small, the increase of gas velocity reduces the relative velocity of gas and liquid, which weakens the gas liquid interaction and eliminates the growth rate and frequency of the dominant wave. Finally the breakup time and breakup length increases. However, when the gas velocity is larger than a critical value, the growth rate and frequency of the dominant surface wave increase rapidly with the increase of gas flow velocity, which in turn lowers the breakup time and breakup length immediately.]]></description>
<pubDate>2019/4/24 14:24:48</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[KANG Zhongtao<sup>1,2,3</sup>, LI Qinglian<sup>2,3</sup> and CHENG Peng<sup>2,3</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>KANG Zhongtao<sup>1,2,3</sup>, LI Qinglian<sup>2,3</sup> and CHENG Peng<sup>2,3</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201902003]]></guid><cfi:id>90</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Structure design for wind′s eye of sabot using genetic algorithm]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201902004]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Aiming at the design requirements of easy separation and light mass for the sabot of integrated launch projectile, an optimization design model was obtained by combining the aerodynamic calculation model by the genetic algorithm, in which the aerodynamic calculation model was established on the basis of the theory of shock and expansion wave through building the parameterized structure model for windward nest. And the discard acceleration and sabot′s mass were used as the indicators to build performance function. Taking the sabot design of armor piercing fin stabilized discarding sabot of medium caliber as an example, the proposed optimization model was used for the optimum structural design of the windward nest, and the simulation model of sabot discard based on dynamic grid technique was adopted to verify the optimality. Simulation results show that the proposed optimization design model can obtain the optimal wind′s eye of the sabot; in view of the existing armor piercing fin stabilized discarding sabot of medium caliber, the sabot structure can be further optimized to improve its rapidity.]]></description>
<pubDate>2019/4/24 14:24:48</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LI Xiangping, LU Junyong, FENG Junhong and DU Peipei]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LI Xiangping, LU Junyong, FENG Junhong and DU Peipei</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201902004]]></guid><cfi:id>89</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Effectiveness analysis of opposing jet thermal protection generating with solid fuel]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201902005]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In order to reduce the size of coolant supply system of opposing jet in hypersonic vehicles, the fuel gas generating with solid fuel was adopted as an opposing jet. The RANS (reynolds-average navier-stokes) equations coupled with the Menter′s SST (shear stress transport) model was employed to solve the opposing jet flow field of hypersonic hemisphere model. The typical results have been validated with experiments performed in the literature. The influence of the high temperature fuel gas on the hemisphere model thermal protection characteristics was analyzed with different flying condition. Results show that the high temperature fuel gas weakens the heat flux reduction of opposing jet, but the peak heat flux exhibits a prominent reduction in contrast to that without injection.The cooling efficiency can be strengthened by increasing the jet pressure. With a reasonable jet pressure, the similar cooling efficiency can be obtained compared with that of the normal coolant and it does not result in additional mass flux. Moreover, the three solid fuel and its combustion temperature are listed. For high Mach flying which is higher than 6, the solid fuel can provide required jet temperature for opposing jet thermal protection system.]]></description>
<pubDate>2019/4/24 14:24:48</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[SHEN Binxian, LIU Weiqiang and YIN Liang]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>SHEN Binxian, LIU Weiqiang and YIN Liang</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201902005]]></guid><cfi:id>88</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Time accuracy analysis of primitive variable-based conservative form governing equations]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201902006]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The governing equations using primitive properties of pressure, velocity and temperature as dependent variables, but constructed in the conservative form can be applied for calculating solutions for steady state problems. When the method was recently used to simulate a canonical shock-tube problem, however, overshoot of temperature was observed after the shock. Moreover, the errors cannot be eliminated by using fine grid, high spatial order of accuracy or any alternative inviscid fluxes schemes that are available, implying the numerical discrepancy may be caused by the method itself. Numerical analysis was conducted on the method using the one-dimensional Euler equations as the model equation system. It can be shown that the numerical error specifically arises from the discretized time terms. A dual-time-looping technique was developed to address the issue. It used conservative variables in physical-time derivatives while primitive variables for pseudo-time terms. An inner iteration procedure within two adjacent physical-time steps were driven until a steady state was reached. The resulting governing equation converged to the corresponding conservative form in time, and the time-accurate solution was recovered.]]></description>
<pubDate>2019/4/24 14:24:48</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[ZHANG Huaibao, WANG Guangxue and WANG Jingyu]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>ZHANG Huaibao, WANG Guangxue and WANG Jingyu</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201902006]]></guid><cfi:id>87</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Fuzzy control for any selected position hovering over  uncontrolled tumbling satellite]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201902007]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The problem of any selected position hovering control of uncontrolled tumbling satellite was researched. A three-dimensional relative motion equation of arbitrary eccentricity was established in the target orbital coordinate system, and the attitude motion characteristics of the uncontrolled tumbling satellite were analyzed. The hovering problem was decoupled into two-dimensional fuzzy control problem of three channels, and the Mamdani fuzzy controller was designed with the channel x as an example. Determining the corresponding fuzzy subset, membership function and fuzzy control rule table, the fuzzy was solved by using the area center method. The control performance of the designed fuzzy controller was verified by numerical simulations.]]></description>
<pubDate>2019/4/24 14:24:48</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LIU Jianghui and LI Haiyang]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LIU Jianghui and LI Haiyang</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201902007]]></guid><cfi:id>86</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[On-board data preprocessing method for path finder of discovering the sky at the super-long wavelengths]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201902008]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[It is focused on CE-4 lunar orbit duel micro satellites mission for super-long wave astronomy. Under the strict resource constraints, the lunar orbit micro-nano satellites have very limited communication bandwidth. In order to maximize valuable scientific data, a method of in-orbit signal preprocessing was presented: the digital down conversion method was used to build the ultra-narrowband filter, which significantly reduces the data rate. The ultra-narrowband filtering scheme can perform comb filtering by increasing the down-conversion filter channels. The ultra-narrowband filter scheme simulations on the field programmable gate array show that the key technical indicators such as flatness and linear phase meet the requirements, and the data rate can be reduced by more than 10<sup>3</sup> times compared with original data rate under the circumstances of the sampling rate is 80 MSPS with baseband bandwidth is 1 kHz.]]></description>
<pubDate>2019/4/24 14:24:48</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[ZHAO Fei<sup>1,2,3</sup>, YAN Jingye<sup>2</sup>, LAN Ailan<sup>1,2</sup> and WU Lin<sup>2</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>ZHAO Fei<sup>1,2,3</sup>, YAN Jingye<sup>2</sup>, LAN Ailan<sup>1,2</sup> and WU Lin<sup>2</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201902008]]></guid><cfi:id>85</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Theoretical analysis of axial residual velocity of penetration with enhanced lateral efficiency pill vertical penetrating thin target]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201902009]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In order to obtain the theoretical model of the axial residual velocity of PELE (penetration with enhanced lateral efficiency projectile) under the condition of vertical penetration, the plane shock wave theory was used to analyze the mechanism of PELE  vertical penetrating metal thin target. According to the penetration model of the flat head projectile, the energy loss during the penetration of PELE  was divided into the following parts: the energy obtained by the annular plug block corresponded to the outer shell and the inner core, the increased internal energy of the outer casing and inner core, the shear energy dissipated in the outer casing. Based on the principle of energy conservation, the theoretical model of axial residual velocity after PELE  vertical penetrating thin metal targets was obtained. To verify the rationality and accuracy of the theoretical model, the corresponding experiments were designed to verify the results. The results show that the calculated results coincide well with the experimental results under different conditions. Therefore, the theoretical model of axial residual velocity of PELE  vertical penetrating thin target can provide guidance and reference for engineering application.]]></description>
<pubDate>2019/4/24 14:24:48</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[DING Liangliang<sup>1</sup>, TANG Wenhui<sup>1</sup>, RAN Xianwen<sup>1</sup>, FAN Zijian<sup>1,2</sup> and XIAO Fan<sup>3</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>DING Liangliang<sup>1</sup>, TANG Wenhui<sup>1</sup>, RAN Xianwen<sup>1</sup>, FAN Zijian<sup>1,2</sup> and XIAO Fan<sup>3</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201902009]]></guid><cfi:id>84</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Research and application of threesection method of load design for a kind of aircraft]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201902010]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In order to solve effectively many shortcoming of traditional load design, a threesection method, namely segment stiffness, segment mass and segment aerodynamics, for the load design of aircraft was presented. The method approximates the actual mass distribution and aerodynamic load distribution of the aircraft. For a simplified aircraft, the modal parameters and the section load were calculated by using the threesection method, the theoretical method and the masspartition method. The results show, the threesection method and the theoretical method are consistent with the model parameters and the calculation principle, which largely can be considered as a method, so their modal parameters and the section load are identical. The load of the left and right section of the masspartition method is pretty inconsistent, and it is not in accordance with the actual load condition. In a word, the threesection method can get a more real and reasonable section load distribution, and the engineering application is simple, reasonable and reliable. At the same time, the method can reduce the design difficulty of missile load and structure.]]></description>
<pubDate>2019/4/24 14:24:48</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[SHANG Lin<sup>1</sup>, ZHANG Hairui<sup>1</sup>, LI Pu<sup>1,2</sup> and MA Youlin<sup>1</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>SHANG Lin<sup>1</sup>, ZHANG Hairui<sup>1</sup>, LI Pu<sup>1,2</sup> and MA Youlin<sup>1</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201902010]]></guid><cfi:id>83</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Numerical investigation of front variable area bypass injector with jet mixing enhancement]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201902011]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In order to improve the mixing performance of fan bypass and CDFS (core driven fan stage) bypass, a innovative configuration of FVABI (front variable area bypass injector) with jet mixing enhancement was proposed. Numerical simulation was performed to investigate mass flow rate characteristic, flow mixing and total pressure loss of FVABI configuration with lobed mixer. Compared with the baseline configuration, the predictions are discussed and several conclusions can be summarized. Firstly, the significant improvement in fan bypass mass flow rate is achieved by jet mixing enhanced configuration at high back pressure operating point. Secondly, the performance is not degraded at low back pressure operating situation, but the total pressure loss is decreased at high back pressure operating point. Finally, the characteristic length of stream-wise vortex is the key to improve mixing performance, and the optimization of lobed mixer is available to match further structural requirement of adjust configuration.]]></description>
<pubDate>2019/4/24 14:24:48</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[WANG Jingyu<sup>1,2</sup>, ZHANG Huaibao<sup>2</sup>, HUANG Guoping<sup>3</sup>, WANG Guangxue<sup>2</sup> and DENG Xiaogang<sup>4</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>WANG Jingyu<sup>1,2</sup>, ZHANG Huaibao<sup>2</sup>, HUANG Guoping<sup>3</sup>, WANG Guangxue<sup>2</sup> and DENG Xiaogang<sup>4</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201902011]]></guid><cfi:id>82</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Effect of back electromotive force on accurate pointing of disturbance-free-payload spacecraft]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201902012]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The back electromotive force of the non-contact actuator in a disturbance-free-payload spacecraft can cause the coupling between payload module and support module, hence can be detrimental to the precise pointing of payload module. To analyze its effect, a coupling dynamics model was established for the disturbancefreepayload spacecraft. In consideration of the cubic architecture disturbance-free-payload-interface, this dynamics model was developed by a combination of the Newton-Euler method with the Lagrange formulation. The output force of the non-contact actuator was derived, which was introduced into the dynamics model of the payload module platform, then the coupling dynamics model with the back electromotive force was obtained. Considering the harmonic vibration caused by the static and dynamic unbalance of the flywheels as the disturbance torque, an on-orbit pointing model for the disturbance-free-payload spacecraft was established in Simulink. The simulation results illustrate that the larger value of the back electromotive force coefficient will cause larger effect on payload module.]]></description>
<pubDate>2019/4/24 14:24:48</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[KONG Xianren, WU Chen, LI Haiqin and YANG Zhenguo]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>KONG Xianren, WU Chen, LI Haiqin and YANG Zhenguo</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201902012]]></guid><cfi:id>81</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Plug and play resolution on 1553B data bus]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201902013]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Based on the traditional 1553B data bus protocol, a new protocol with plug and play features was designed by adding remote terminal EDS (electronic data sheet) and procedure of transferring EDS. According to this protocol, the plug and play resolution of 1553B bus controller was designed, including constructing a bus list algorithm with the remote terminals plug in，management data structure, and dynamic operation and control bus list method. The constructing bus list algorithm uses remote terminal EDS to analyze, calculate and transform an old bus list to a new one, to satisfy remote terminals′ communication requirements. A management data structure is used for analyzing and storing bus list information during initialization phase， to increase efficiency of operation control and data exchanging. Dynamic operation and control bus list method adopts main bus list with plug in messages method. The timeliness and use cases of the resolution were evaluated. The results show that its time of bus cycle and time of remote terminal plugged into the system can be accepted. The resolution can remain stable in the communication process, and provide flexibility for plug and play needs. In CCSDS-SOIS architecture, 1553B data bus is one of the subnetworks on the bottom layer. With plug and play features, it can be extended to support constructing plug and play system in higher layer.]]></description>
<pubDate>2019/4/24 14:24:47</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LYU Liangqing<sup>1,2</sup> and AN Junshe<sup>1</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LYU Liangqing<sup>1,2</sup> and AN Junshe<sup>1</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201902013]]></guid><cfi:id>80</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Sliding mode control for trajectory tracking of stratospheric airships in wind field]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201901001]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In order to realize the controllable flight of stratospheric airships during floating, the sliding mode control for lateral trajectory tracking in wind field was researched. The dynamic models of the stratospheric airship during floating were established, and the models were linearized by using linear perturbation theory. The sliding mode controller for lateral trajectory tracking was designed. Considering that this method was insensitive to external perturbation, the trajectory tracking for linear formation and circular was simulated. Simulation results show that the robustness and response characteristic of the trajectory tracking method based on sliding mode control are both satisfactory, and the control accuracy is high in wind field.]]></description>
<pubDate>2019/3/15 11:33:33</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[YANG Xixiang<sup>1,2</sup> and ZHANG Jiashi<sup>1</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>YANG Xixiang<sup>1,2</sup> and ZHANG Jiashi<sup>1</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201901001]]></guid><cfi:id>79</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Station-keeping performance of novel near-space aerostat in quasi-zero wind layer]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201901002]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[A novel near-space aerostat based on quasizero wind-layer field for station-keeping was investigated. The working principle and system composition of the aerostat were introduced first. After that, a model comprising of dynamics, altitude control and energy circle was established. The properties of station-keeping and energy circle of the aerostat were studied in two typical working modes: flight speed limitation and north-south displacement limitation. With the weather input of Changsha, it is found that, compared with uncontrolled free-flying mode, the aerostat can achieve long resident in a 100 km diameter range under both working modes. Moreover, the energy consumption of the aerostat with flight speed limitation mode is lower than that of the other mode.]]></description>
<pubDate>2019/3/15 11:33:33</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[DENG Xiaolong<sup>1</sup>, LI Kui<sup>1</sup>, YU Chunrui<sup>2</sup>, YANG Xixiang<sup>1</sup> and HOU Zhongxi<sup>1</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>DENG Xiaolong<sup>1</sup>, LI Kui<sup>1</sup>, YU Chunrui<sup>2</sup>, YANG Xixiang<sup>1</sup> and HOU Zhongxi<sup>1</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201901002]]></guid><cfi:id>78</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Power analysis of stratospheric airship′s solar array system]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201901003]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The power of airship′s curved solar array is closely related to the position of airship, time of flight, flight of attitude, layout of solar array and so on. Through the analysis of solar radiation model, and combined with the variation of azimuthal angle in the course of stratospheric airship′s flight, the projection was used to calculate the power of curved solar array, thus the dynamical power generation of the airship was calculated. The analysis results show that the projection in horizontal is the main component of curved solar array′s power, which is little influenced by airship′s azimuthal angle; the power of projections in vertical is smaller, which is more easily affected by airship′s azimuthal angle.]]></description>
<pubDate>2019/3/15 11:33:33</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[ZHU Bingjie, YANG Xixiang, MA Zhenyu and DENG Xiaolong]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>ZHU Bingjie, YANG Xixiang, MA Zhenyu and DENG Xiaolong</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201901003]]></guid><cfi:id>77</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Steady climbing approach of near-space solar aircraft with wing morphing]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201901004]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[To satisfy the rigorous constraint of energy balance, near-space solar aircrafts are usually designed with large aspect ratio and lightweight structures, which leads to a very slow airspeed and a bad flight safety in low altitude airspace. For matching the aerodynamic performances at nearspace working point and in low-altitude climbing process, a climbing approach of solar aircraft based on active morphing was proposed. The aerodynamic and propulsion modeling methods were researched. The flight safety and maneuverability of the pitch, roll and yaw attitude channels were analyzed in quantification. As a result, a climb process with the wing gradually stretching was decided, in which the level flight thrust and power costs were checked. Results show that the stability and maneuverability in low altitude flight are effectively improved, and the cost of power is increased by the wing morphing.]]></description>
<pubDate>2019/3/15 11:33:33</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[GUO Tianhao, HOU Zhongxi, WANG Peng and GAO Jun]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>GUO Tianhao, HOU Zhongxi, WANG Peng and GAO Jun</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201901004]]></guid><cfi:id>76</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[CH-PLIF imaging of flame heat-release structures in supersonic combustion]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201901005]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Scramjet engine is one of the most important components of air-breathing hypersonic vehicles, and the research on flame structures in the combustion chamber of scramjet engines plays a significant role in studying the mechanism of flame stabilization of the supersonic combustion. Two-dimensional distributions of CH were measured at a direct connect test facility using the PLIF (planar laser-induced fluorescence) technique to visualize the flame heat-release structures in a cavity-stabilized scramjet combustor. Verification and optimization of the CH-PLIF technique were conducted in a methane/air premixed lowspeed flame generated by a jet flame burner. Two-dimensional distributions of flame heat-release structures in the scramjet combustor were achieved by using the CH-PLIF technique. OH-PLIF images and CH chemiluminescence images were also performed in the scramjet combustor to compare these images with the CHPLIF images. Experimental results show that the heat-release zones of the low-speed premixed jet flames can become distorted, wrinkled and separated. The heat-release zones are highly wrinkled with the increasing Reynolds numbers. The heat-release zones with a thickness of 0.5~6.5 mm in the cavity-stabilized scramjet combustor become highly distorted and wrinkled, and the separation of the heat-release zones can be observed. It is found that the CH-PLIF technique is able to visualize the heat-release zones in cavity-stabilized scramjet combustors and can play a promising role in understanding cavity stabilization mechanisms of the supersonic combustion.]]></description>
<pubDate>2019/3/15 11:33:33</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LIANG Jianhan<sup>1</sup>, LI Yun<sup>1</sup>, SUN Mingbo<sup>1</sup>, WU Ge<sup>1</sup>, ZHU Jiajian<sup>1</sup>, GAO Qiang<sup>2</sup> and LI Bo<sup>2</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LIANG Jianhan<sup>1</sup>, LI Yun<sup>1</sup>, SUN Mingbo<sup>1</sup>, WU Ge<sup>1</sup>, ZHU Jiajian<sup>1</sup>, GAO Qiang<sup>2</sup> and LI Bo<sup>2</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201901005]]></guid><cfi:id>75</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Numerical simulation of booster separation for an air-breathing hypersonic vehicle]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201901006]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Aiming at the special environment of the air-breathing hypersonic ramjet flight test, especially the booster separation conditions, the multi-body separation of an axisymmetric hypersonic aircraft was studied. Six degrees of freedom solver and local mesh reconstruction based on non-structured mesh method were proposed to simulate the separation process. Results include motion parameters of the booster and the aerodynamic characteristics ranging from 0 ms to 300 ms for the aircraft under the weak perturbance states.  Meanwhile, the trajectory curve of separation was demonstrated. Finally, the feasibility of the subsequent scheme was estimated and the optimal conditions for the separation reached requirement of mild interference.]]></description>
<pubDate>2019/3/15 11:33:33</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[WEN Xun, LIU Jun and XIA Zhixun]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>WEN Xun, LIU Jun and XIA Zhixun</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201901006]]></guid><cfi:id>74</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Trajectory multi-objective optimization for hypersonic telescopic wing morphing aircraft]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201901007]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In order to explore the application of morphing technology in hypersonic aircraft, a hypersonic morphing aircraft based on telescopic wing was proposed. Then the trajectory of glide phase was optimized through multi-objective optimization method. Firstly, the aerodynamic characteristics of different telescopic morphing phases were offered, the 3- degree of freedom dynamic model of free glide phase and the heat flux model of the leading edge of the wing were built. In the MOP (multi-objective optimization problem), the two optimization objectives were the range of trajectory, and the total heat of the leading edge of the wing. The optimization variables include the Mach numbers when the aircraft was morphing, and the angle of attack of different phases. MOP was solved by using the MOEA/D (multi-objective evolutionary algorithm based on decomposition). Numerical simulation results show that the proposed method can obtain the Pareto Front. Also, compared with the non-morphing aircraft, the aircraft can achieve a larger range and a smaller total heat of the leading edge of the wing.]]></description>
<pubDate>2019/3/15 11:33:33</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[PENG Wuyu<sup>1</sup>, YANG Tao<sup>1</sup>, WANG Changyue<sup>2</sup>, FENG Zhiwei<sup>1</sup> and TU Jianqiu<sup>2</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>PENG Wuyu<sup>1</sup>, YANG Tao<sup>1</sup>, WANG Changyue<sup>2</sup>, FENG Zhiwei<sup>1</sup> and TU Jianqiu<sup>2</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201901007]]></guid><cfi:id>73</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Reduced kinetic model for supersonic combustion of vaporized kerosene]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201901008]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In order to explore the chemical kinetics process of kerosene combustion in scramjet combustor, a detailed chemical reaction model for the combustion of RP-3 surrogate fuel was simplified to obtain a new reduced model (26 species and 89 reactions) based on the sensitivity analysis and reaction path analysis, and the combustion characteristics of supersonic reacting flow field were depicted. The ignition and combustion characteristics of this surrogate fuel under various conditions were simulated by using the reduced reaction model，and the simulation results were compared with the experimental data and the calculated results by the detailed reaction model. Furthermore, numerical simulations were implemented by using a coupled nonequilibrium reaction solver with the proposed reduced model, and the combustion characteristic of a scramjet combustor with single-side cavity was analyzed in detail. The results indicate that the reduced model can represent the ignition and combustion characteristic of the detailed model to some extent. And the proposed reduced chemical kinetic model predicts the myriad details of the reacting flow field accurately, including the distributions of major species, such as alkenes and cycloalkanes. At the same time, the number of species involved in the reduced model is much fewer, and the reduced model can improve the combustion simulation efficiency.]]></description>
<pubDate>2019/3/15 11:33:33</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[FAN Xiaofeng, WANG Jiangfeng, ZHAO Faming and YANG Tianpeng]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>FAN Xiaofeng, WANG Jiangfeng, ZHAO Faming and YANG Tianpeng</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201901008]]></guid><cfi:id>72</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Shape design of zero pressure high altitude balloon and sensitivity analysis of key parameters]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201901009]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[High altitude balloon provides a reliable platform for high altitude scientific experiments. The shape of the balloon is directly related to the whole process of making and flying. The multiple-shooting method was combined with the sequence of two quadratic programming method, and the under-expansion shape and optimum-expansion shape were obtained. In addition, the finite element method was used to analyze the stability and stress and strain of the sphere to verify the correctness of the derived sphere. On this basis, the sensitivity analysis and related application of the key parameters affecting the balloon shape were carried out, and the effects of balloon load, flight altitude and temperature difference between day and night on the balloon shape were obtained quantitatively.]]></description>
<pubDate>2019/3/15 0:00:00</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[YANG Yanchu<sup>1,2</sup>, ZHANG Hangyue<sup>1,2</sup> and ZHAO Rong<sup>1,2</sup>]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>YANG Yanchu<sup>1,2</sup>, ZHANG Hangyue<sup>1,2</sup> and ZHAO Rong<sup>1,2</sup></atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/201901009]]></guid><cfi:id>71</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Review of multi-modal image matching assisted inertial navigation positioning technology for unmanned aerial vehicle]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202006001]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[High-precision positioning and navigation in GPS(global positioning system) denied environments is a key technology for aircraft achieving autonomous scout, cruise, and strike. Vision navigation has the advantages of passive-type, low cost, and avoidable accumulated errors avoidable, etc. The fusion of vision and inertial navigation can give full play to their advantages and achieve the purpose of high-precision positioning. Firstly, the development of aircraft positioning technology based on multi-modal image matching assisted inertial navigation was summarized. Then this technology was elaborated in five aspects:the vision-internal calibration, multi-modal image matching, attitude algorithm, data fusion, and back-end optimization. Finally, four possible future directions were proposed as follows, two types of passive positioning combined navigation systems based on deep learning, multi-modal image matching and inertial navigation. The four possible future directions provide a reference for realizing multi-modal image matching assisted inertial navigation aircraft positioning technology.]]></description>
<pubDate>2020/12/2 0:00:00</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LUO Shibin, LIU Haiqiao, HU Maoqing, DONG Jing]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LUO Shibin, LIU Haiqiao, HU Maoqing, DONG Jing</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202006001]]></guid><cfi:id>70</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Influence of drive control on dynamic characteristics of solar array drive system]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202006002]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Accurate prediction of dynamic characteristics is an indispensable research foundation for the disturbance mechanism and vibration control of SADS(solar array drive system). The equivalent mechanical parameters of the drive mechanism were deduced with the consideration of drive control, the equivalent dynamics-characteristics analysis model of SADS was built and verified via simulation and experiment, the influence of the drive speed and control gains on the equivalent mechanical parameters of drive mechanism and dynamic characteristics of SADS was discussed. The results show that the equivalent analysis model can accurately predict the dynamic characteristics of SADS with different drive speeds and control gains, and the error between the analysis results and the test data is less than 10%. The equivalent damping of the drive mechanism cannot be affected by the drive speed and control gain, but the equivalent stiffness decreases with the decrease of the control gain and the increase of the drive speed. The drive control gradually becomes an important factor affecting the dynamic characteristics of SADS with the increase of the drive speed.]]></description>
<pubDate>2020/12/2 10:56:12</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[ZHU Shiyao, GUO Xin, LEI Yongjun]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>ZHU Shiyao, GUO Xin, LEI Yongjun</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202006002]]></guid><cfi:id>69</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Manned lunar mission planning based on once low earth orbit and twice low lunar orbit rendezvous and dockings]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202006003]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Aiming at the complex problem of matching flight windows and orbits connection due to the multiple flight stages, long duration and complicated constraints of the manned lunar mission based on once LEO (low earth orbit) and twice LLO (low lunar orbit) RVDs (rendezvous and dockings), a design strategy of connecting the full-mission nominal flight windows and orbits with the combining layered decomposition and the forward and reverse design approach were proposed. The characteristics and application prospect of the manned lunar mission based on once LEO and twice LLO RVDs were introduced, and the basic mission requirements and engineering constraints were supposed. The effectiveness of the proposed method was verified by simulation. The nominal flight orbital elements and windows of the manned lunar mission based on once LEO and twice LLO RVDs can be responded rapidly.]]></description>
<pubDate>2020/12/2 10:56:12</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[HE Boyong, SHEN Hongxin, PENG Qibo]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>HE Boyong, SHEN Hongxin, PENG Qibo</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202006003]]></guid><cfi:id>68</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Gyro/double star sensors integrated attitude determination for CubeSat]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202006004]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[For the problem that the measurement precision of the rotation angle about line-of-sight vector of single star sensor is relatively low, a method of utilizing measurement from MEMS(micro-electro-mechanical system) gyro and two simultaneously operating star sensors to obtain accurate attitude knowledge of CubeSat was proposed. Based on the idea of averaging two quaternions, two attitude determination schemes called centralized filter and decentralized filter were drawn up by using MEKF(multiplicative extended Kalman filter). Simulation results indicate that attitude determination performance is improved effectively by the presented method and it has higher precision and quicker convergence, under the circumstance of utilizing low-cost and low-accuracy attitude sensors and traditional attitude filtering algorithm. It provides a feasible reference for low-cost and high-precision attitude determination of CubeSat, and has certain engineering application value.]]></description>
<pubDate>2020/12/2 10:56:12</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[MA Haining, LU Zhengliang, ZHANG Xiang, LIAO Wenhe]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>MA Haining, LU Zhengliang, ZHANG Xiang, LIAO Wenhe</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202006004]]></guid><cfi:id>67</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Modified algorithm of triangle star identification based on radial feature]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202006005]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Triangle star identification has strong reliability and operability, and is still widely used at present, but the triangle star identification algorithm poses problems of redundant matching and wrong identification. The radial feature quantity of the star point was constructed by the geometric distribution of the star point. The star point was initially identified, and the navigation star corresponding to the star point was limited to several navigation stars by initial recognition. On the basis of initial identification, the triangle segmentation identification algorithm was used to identify the initial recognition result again, which improves the pertinence and efficiency of star map identification. The experimental results show that when the new algorithm is used to identify the stars, the accuracy and rapidity of star identification are improved.]]></description>
<pubDate>2020/12/2 10:56:12</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LIU Xianyi, ZHANG Zhili, ZHOU Zhaofa, CHANG Zhenjun]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LIU Xianyi, ZHANG Zhili, ZHOU Zhaofa, CHANG Zhenjun</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202006005]]></guid><cfi:id>66</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Sensitive feature extraction and anomaly detection method based on referenced manifold spatial fusion learning]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202006006]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Aiming at the problem of low recognition rate of heterogeneous patterns caused by the characteristics of small sample size, strong impact, short response period and wide resonance frequency bandwidth of telemetry vibration signals, a method for sensitive feature extraction and anomaly detection of telemetry vibration signal based on referenced manifold spatial fusion learning was proposed. The multi-scale analysis method was used to decompose the signals orthogonally into each in the scale band; the multi-scale feature was extracted to construct the high-dimensional feature set. The same normal signal sample was combined with the same type of abnormal sample to establish the exclusive reference model unit, and the linear manifold learning was used to obtain the multi-scale manifold feature difference of each reference model unit to enhance the sensitivity of anomalous features. The projection matrix of each reference model unit was used to enhance the original feature set and obtain the low-dimensional multi-scale sensitive manifold feature. The input to the classifier was used to realize the state recognition of the unknown sample. The measured signal processing results verified the effectiveness of the algorithm.]]></description>
<pubDate>2020/12/2 10:56:12</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LIU Xue, SUN Ao, LI Dong]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LIU Xue, SUN Ao, LI Dong</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202006006]]></guid><cfi:id>65</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Research progress of the underwater gravity-aided navigation based on the information of aerospace-marine integration]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202003006]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The accurate navigation of the underwater vehicle plays an important role in the process of the ocean utilization and development. The problem of restraining the accumulation errors of the underwater navigation over time was discussed and analyzed in detail. Firstly, the development history of the inertial devices was briefly described. Secondly, the advantages and disadvantages of each navigation system were compared in detail, the research status of the gravity-aided navigation at home and abroad were introduced, and the demand for the high-precision navigation of the underwater vehicles and the scientific problems of insufficient spatial resolution of the global marine gravity reference map were analyzed. Finally, the idea and technical route of obtaining the high spatial resolution and high precision global marine gravity reference map by GNSS-R altimetry constellations are proposed in order to improve the accuracy of the underwater gravity-aided navigation.]]></description>
<pubDate>2020/7/6 0:00:00</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[ZHENG Wei, LI Zhaowei, WU Fan]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>ZHENG Wei, LI Zhaowei, WU Fan</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202003006]]></guid><cfi:id>64</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Effect of channel mismatch on the anti-jamming performance of GNSS adaptive antenna arrays]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202003007]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Satellite navigation receivers are highly susceptible to electromagnetic interference, and array-based space-time or space-frequency adaptive processing has been proved to be the most effective anti-jamming method. In actual engineering implementation, the channel mismatch is inevitable. Thus in this paper, the impact of channel mismatch on the performance of GNSS antenna array was evaluated according to the statistical evaluation method. The results show that, group delay bias and amplitude mismatch between channels are the two main factors leading to the deterioration of anti-jamming performance. The influence of the former can be eliminated by increasing the number of taps of space-time filter, while the latter is not sensitive to the number of taps and the necessary calibration is required.]]></description>
<pubDate>2020/7/6 0:00:00</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[CHEN Feiqiang, LU Zukun, CHEN Lei, LI Zhengrong, SUN Guangfu]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>CHEN Feiqiang, LU Zukun, CHEN Lei, LI Zhengrong, SUN Guangfu</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202003007]]></guid><cfi:id>63</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Satellite networks coordination situation assessment method based on convolution neural network]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202003008]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In order to fully explore the use of massive satellite network data, improve decision-making efficiency,and strengthen the analysis methods of spatial frequency and orbit resource acquisition and storage, especially for the GSO (geostationary satellite orbit) resource selection problem, a satellite network situation assessment strategy based on machine learning algorithm was proposed. By analyzing the characteristics of satellite network coordination factors, the CNN (convolutional neural network) was selected as the target algorithm model, and the training data set and label rules of the algorithm model were established. The data is reduced by the split information gain measurement method and a CNN evaluation model was established. Afterwards, a verification analysis was performed. Results show that the CNN model has a correct rate of 80% or more for the satellite network coordination situation assessment problem, and has high evaluation efficiency. Moreover, with the increase of the amount of data, the evaluation effect of CNN is gradually improved, which indicates the proposed method is an effective evaluation method for coordination situation analysis and resource reserve in satellite networks.]]></description>
<pubDate>2020/7/6 0:00:00</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[GAO Xiang, LIU Heguang, CHEN Zhimin, YAO Xiujuan, WANG Chunmei]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>GAO Xiang, LIU Heguang, CHEN Zhimin, YAO Xiujuan, WANG Chunmei</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202003008]]></guid><cfi:id>62</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Impact of gas ejection interaction with hypersonic mainstream at different ejecting states]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202003009]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In order to study the impact of different ejecting state on aerodynamic heating of hypersonic aircrafts,the square/circle hole ejecting under hypersonic flow condition was numerically simulated. The impacts of ejecting pressure, ejecting velocity and ejecting direction to the main flow field were discussed and the flow field structure, wall heat flux and center line temperature at different ejecting state were obtained. The results show that gas ejection can relieve the aerodynamic heating situation of wall to some extent. The cooling effect at whole wall ejection is remarkable. And the wall heat flux reduces nearly two-thirds when the ejecting velocity is about 1 m·s-1. Moreover, at high ejecting velocity (Ma>1), the cooling effect is strengthened by increasing the ejecting pressure and velocity appropriately. At low ejecting velocity (Ma<0.6), the ejection flows within the boundary layer, and has a weak influence on the main flow field structure; the greater the ejecting velocity is, the bigger the range of cooling is, and the better the cooling effect is. The cooling effect of downstream is better when the ejecting direction is acute angle, and the cooling effect of upstream is better when the ejecting direction is obtuse angle.]]></description>
<pubDate>2020/7/6 0:00:00</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[WANG Liyan, TAN Meijing, NIE Liang, JIANG Yunsong, YUAN Ye, WANG Zhenfeng]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>WANG Liyan, TAN Meijing, NIE Liang, JIANG Yunsong, YUAN Ye, WANG Zhenfeng</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202003009]]></guid><cfi:id>61</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[A survey of non-cooperative target capturing methods]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202003010]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[With the increase of space accidents and failed spacecraft, the orbital resources are dwindling. Now many countries in the world are developing on-orbit service and space debris removal. As one of the most critical technology, non-cooperative target capture has become a focus in the field of space research in recent years. At present, domestic and foreign institutions have conducted in-depth studies on non-cooperative targets, while various capturing methods were proposed, and great progress was made. Firstly, the non-cooperative target was classified, and then the latest situation of non-cooperative target capture technology at home and abroad was introduced with the existing capturing methods. The principle scheme is summarized, and the capturing methods and key technologies are analyzed, which will offer a perspective for future research.]]></description>
<pubDate>2020/7/6 0:00:00</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[SUN Yongjun, WANG Qian, LIU Yiwei, XIE Zongwu, JIN Minghe, LIU Hong]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>SUN Yongjun, WANG Qian, LIU Yiwei, XIE Zongwu, JIN Minghe, LIU Hong</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202003010]]></guid><cfi:id>60</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Modeling and solving for task dispatch problem of vehicular optical observation equipment]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202105001]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[For the purpose of raising observation effectiveness and improving observation capability, the problem of observation task dispatch of vehicular optical observation equipment was addressed. The problem was modeled as one that aims to find the optimal observation plan. The mathematical description of observation plan was presented, the constraints which a plan must satisfy were summarized and the metrics which testify the plan quality were proposed. The multiple-attributes-decision-making method was employed to calculate the overall efficacy of plans and the optimal plan was obtained by sorting. Sample simulation showed the effectiveness of the proposed approach. The model and method fulfilled in this paper were novel and extendible, which is valuable for the application of vehicular optical observation equipment.]]></description>
<pubDate>2021/9/29 9:04:40</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[CHAI Hua, SONG Xumin, ZHAO Qian, HU Tao]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>CHAI Hua, SONG Xumin, ZHAO Qian, HU Tao</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202105001]]></guid><cfi:id>59</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Numerical study on the aerodynamic characteristics of the rotating projectile based on Bang-Bang control method]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202105002]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[To study the effect of Bang-Bang controlled canard on aerodynamic characteristics of the rotating projectile, the nested grid in CFD software was used to simulate the spinning of missile and the deflection of canard. By this method, aerodynamic characteristics of the Bang-Bang controlled rotating missile at different angles, Mach numbers and rotation speeds were numerically simulated, and the aerodynamic law of the rotating missile was obtained. The research shows that the immediate change of lateral forces will take place in projectile body and tail fin, due to the variation in canard washing current direction which coupled the missile spin. Compared with those without canard control, the periodic average lateral force coefficient under control decreases, while the normal force coefficient increases. Due to lateral force, the net force in a period deviates from the vertical direction, and the deviation angle of which decreases with the increase of Mach number, spin rate and attack angle.]]></description>
<pubDate>2021/9/29 0:00:00</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[XU Yihang, CHEN Shaosong, ZHOU Hang]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>XU Yihang, CHEN Shaosong, ZHOU Hang</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202105002]]></guid><cfi:id>58</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Maneuver trajectory prediction of target based on improved KELM and ensemble learning theory]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202105003]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In order to improve the forecasting accuracy and generalization ability, a target maneuver trajectory forecasting approach based on ensemble learning theory and KELM (kernel extreme learning machine) optimized by the modified bat-inspired algorithm was proposed. A KELM model optimized by improved bat-inspired algorithm was constructed. Combined with the ensemble learning theory, the improved KELM neural network was regarded as weak predictor to generate strong predictor, the structure and parameters of the strong predictor were continuously optimized through training, and a target maneuver trajectory prediction model based on the ensemble learning theory was obtained. Based on samples of different sizes, the prediction performance of the model proposed in this paper was compared with BP (back propagation) neural network, support vector machine and extreme learning machine. The simulation results show that the generalization ability and prediction accuracy of the prediction model proposed is good.]]></description>
<pubDate>2021/9/29 9:04:40</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[KOU Yingxin, XI Zhifei, XU An, LI Zhanwu, YANG Aiwu]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>KOU Yingxin, XI Zhifei, XU An, LI Zhanwu, YANG Aiwu</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202105003]]></guid><cfi:id>57</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Numerical simulation on spray combustion responses to acoustic excitation in a gas-liquid pintle rocket engine]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202105004]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In order to investigate the acoustic oscillation characteristics of gas-liquid pintle rocket engine and provide a reference for later optimization designs, a LOX/GCH<sub>4</sub> pintle engine with rectangular combustor was manufactured. The Euler-Lagrange method was used to simulate the acoustic response produced by transverse velocity disturbance, and the effect of acoustic excitation frequency on the transient spray combustion process was studied before fire tests. Numerical results show that the adopted transverse velocity disturbance can produce the first-order transverse acoustic oscillation response with the same oscillation frequency in the combustion chamber. The response of spray combustion to acoustic excitation can be greatly affected by the relative size of the disturbance frequency and the combustor natural frequency of first-order transverse oscillation mode. When the disturbance frequency and the natural frequency are equal, the pressure and heat of reaction oscillate in phase with the velocity disturbance in the first half of combustor, and the significant increase of pressure oscillation amplitude also causes spray flame to swing synchronously. Meanwhile, there is a tendency to shift from diffusion combustion to premixed combustion in the combustor. Methane burns completely in the shorter distance and the combustor temperature tends to be uniform.]]></description>
<pubDate>2021/9/29 9:04:40</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[JIN Xuan, SHEN Chibing, LIN Sen, YANG Lintao]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>JIN Xuan, SHEN Chibing, LIN Sen, YANG Lintao</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202105004]]></guid><cfi:id>56</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Numerical simulation on convective heat transfer between high-temperature gas and regenerative cooling panels of different configurations]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202105005]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The three-dimensional coupled heat transfer between high-temperature gas, regenerative cooling panels with parallel cooling channels were numerically investigated, in which kerosene of supercritical pressure was used as the coolant. Combined with theoretical analysis, the influence of panel configuration was studied and discussed. Results indicate that the temperature of the gas heated surface rise with the thickness of gas side wall, the width and height of the cooling channels, while heat flux of the gas heated surface decreases with the increase of these parameters. It was found that the percentage of the heat absorbed by kerosene from the bottom walls, side walls and top walls of the cooling channels hardly changes with the thickness of gas side wall, while it changes with the variation of width and height of the cooling channels.]]></description>
<pubDate>2021/9/29 9:04:40</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[HU Jiangyu, WANG Ning, ZHOU Jin, PAN Yu]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>HU Jiangyu, WANG Ning, ZHOU Jin, PAN Yu</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202105005]]></guid><cfi:id>55</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Experimental study on the coupling effect of ventilated cavity and supersonic tail jet]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202105006]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Based on an open water tunnel, an experimental system for the coupling of ventilated cavity and supersonic jets was constructed. Four variable length experimental models were designed, focusing on the influence of the relative position of the jet and the ventilated cavity on the interaction mechanism. For different experimental models, the ventilation flow and jet flow were changed to obtain the dynamic process of the evolution of the cavity interface under different working conditions. Experiment observed three distinct mechanisms, which were divided into the following types:the jet fully inflated the cavity and the jet partially deflated the cavity; the jet fully deflated the cavity. By combining the experimental results and Paryshev′s theory, the calculation model of the cavity size and critical transition conditions for different mechanism were further constructed. When Ｊ≤0.1, the cavitation length can be described by the classic cavity empirical formula; When 0.1<Ｊ<1.5, the cavitation length is divided into two parts:the model length and the tail cavity length, and the length of the closed cavity from the nozzle outlet is only related to the parameter Ｊ; When Ｊ≥1.5, the ventilated cavity closes at the tail of the nozzle, the cavity length is approximately equal to the model length.]]></description>
<pubDate>2021/9/29 0:00:00</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[ZHAO Xiaoyu, XIANG Min, LIU Bo, ZHANG Weihua]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>ZHAO Xiaoyu, XIANG Min, LIU Bo, ZHANG Weihua</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202105006]]></guid><cfi:id>54</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Particle packing model of composite solid propellant and its statistical analysis]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202105007]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Composite solid propellant is a kind of composite material with high packing fraction. It has the characteristic of heterogeneity in meso-scale because of the random distribution of oxidizer and metal particles in the matrix. Effects of particle gradation, spatial distribution and content must be taken into consideration while studying the combustion characteristics and mechanical property of the solid propellant in meso-scale. A random sphere packing model of nitrate ester plasticized polyether propellant based on molecular dynamics method was built. Monte-Carlo simulation was used to calculate the two-point correlation function of the random sphere pack. The effects of packing fraction, particle gradation and particle size on the two-point correlation function were studied. From the statistical significance, to obtain the minimum size of representative volume element with the characteristics of ergodicity, statistical homogeneity and isotropy can effectively reduce the calculation cost of subsequent research. The meso-scale propellant model established in this research is important and basic for the study on the complex nonlinear processes of the composite solid propellant such as combustion, decomposition, agglomeration.]]></description>
<pubDate>2021/9/29 0:00:00</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[YAN Xiaoting, XIA Zhixun, NA Xudong, SHA Benshang]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>YAN Xiaoting, XIA Zhixun, NA Xudong, SHA Benshang</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202105007]]></guid><cfi:id>53</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Fast prediction for footprint of hypersonic glide reentry vehicle]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202101001]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Prediction for footprint of incoming hypersonic glide reentry vehicle as a defensive party has such problems as insufficient prior information and high timeliness requirement for solution. A fast prediction method of footprint based on optimal flight hypothesis was proposed:only if the position, velocity and maximum lift-drag ratio of the target at the current time are known (which can be obtained by real-time trajectory estimation based on radar detection data), based on the equilibrium glide hypothesis and the Egers solution of the maximum cross range, the coordinates of the maximum longitudinal range and cross range end points can be obtained respectively; then in the two-dimensional plane of longitude and latitude, the footprint can be approximated as a semi-elliptic area with the intersection of the two maximum cross range end points as the short axis and the distance from the maximum longitudinal range end point to the short axis as the half-long axis. The simulation results show that, compared with the traditional numerical optimization method and the constant bank angle method, the proposed method has the advantages of less prior information, higher accuracy and less computation, and can meet the real-time requirements.]]></description>
<pubDate>2021/1/26 15:57:45</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[WU Nan, WANG Feng, ZHAO Min, MENG Fankun]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>WU Nan, WANG Feng, ZHAO Min, MENG Fankun</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202101001]]></guid><cfi:id>52</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Mini-missile longitudinal control system design with disturbance rejection]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202101002]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Aiming at solving the disturbance problem faced by the mini-missile as well as following practical classic linear frequency-domain design methods, a promoted disturbance estimation and rejection control method based on H<sub>∞</sub>synthesis and equivalent-input-disturbance was proposed to apply to the missile longitudinal control system design. The mismatched disturbance problem was resolved by the establishment of equivalent-input-disturbance system. A disturbance filter and a composite controller were designed through H<sub>∞</sub>optimization to realize the disturbance estimation and compensation and simultaneously to guarantee the overall stability of the system. The feasibility and effectiveness of the method was validated by numerical simulation and bias comparison with extended state observer based control and disturbance observer based control methods.]]></description>
<pubDate>2021/1/26 0:00:00</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LI Tong, MENG Zhipeng, LYU Liang, ZHANG Shifeng]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LI Tong, MENG Zhipeng, LYU Liang, ZHANG Shifeng</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202101002]]></guid><cfi:id>51</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[High precision time synchronization and public information distribution for space utilization payload]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202101003]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[For payloads with high requirements in time reference precision and public information, the general time data and public telemetry data provided by spacecraft platform is not sufficient. In contrast, some functional payloads have ability to output high-precision time and state measurement information, but their hardware interface resources are limited. To synchronize high-precision clock source of functional payload to other payloads with needs, the IEEE 1588v2 time synchronization protocol can be stacked into an optical fiber FC-AE-1553 network. Measurement information provided by the functional payload, such as location, attitude and orbit data, was then able to be sent to each payload NT terminal nodes distributed in whole network. A protocol was proposed to meet the demand of high precision time and public information of payloads, and also to avoid the resource information interface limitation of functional payloads. Design verification was carried out and the result shows that time data and public information supplied by the functional payload can successfully be sent to each node after the FC-AE-1553 network synchronization. The precision of data accepted by payload is three orders of magnitude higher compared with the information source of spacecraft platform, and the accuracy of UTC(universal time coordinated) time accepted is up to 100 ns.]]></description>
<pubDate>2021/1/26 15:57:49</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[QIU Aihua, QIAO Kuangyi, CHEN Yinyuan, ZHANG Tao〖JZ]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>QIU Aihua, QIAO Kuangyi, CHEN Yinyuan, ZHANG Tao〖JZ</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202101003]]></guid><cfi:id>50</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Shape optimization design for vehicles based on aerodynamic and trajectory integrated model]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202101004]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In order to improve the effect of the shape optimization design, the influence of the flight profile with large-airspace and wide speed range for new type of vehicles on aerodynamic shape was studied and a new shape optimization design method based on the aerodynamic and trajectory integrated model was proposed. By this method, the aerodynamic and trajectory integrated model was constructed by using the CST(class/shape function transformation) parametric method, engineering estimation and the Radau pseudospectral method. To implement the efficient global optimization within multi-constraints, an aerodynamic shape optimal design method based on Kriging surrogate model was proposed after clearing the optimization target and constraint condition. The shape optimization design for a type of lifting body vehicles was carried out. It is shown that the aerodynamic and trajectory feature of large-airspace and wide speed range can be better described, and the accuracy and performance of the shape optimization design are improved, which can provide technical support for the conceptual aircraft design.]]></description>
<pubDate>2021/1/26 15:57:51</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[ZHANG Hairui, QIN Meng, ZHOU Guofeng, WANG Hao]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>ZHANG Hairui, QIN Meng, ZHOU Guofeng, WANG Hao</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202101004]]></guid><cfi:id>49</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Detection method for intersection points based on gradient-histogram]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202101005]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[A detection method for intersection points based on gradient-histogram was proposed. The feature descriptor was generated for each image pixel using gradient of neighborhood pixels. The candidate intersection points were taken from all image pixels according to specific constraints. The candidate intersection points were clustered into different categories based on Euclidean distance. The subpixel positions were computed for each intersection points by the weighting method. The proposed method was validated by simulations. The results show that the method can be used to detect the intersection points of crossing angle 65°~90° with the precision of 0.6 pixel and the detection rate exceeds 90%, and the precision and detection rate of proposed method is invariant to image rotating. The method is robust to image noise and can satisfy the need of detecting intersection points on image under normal prospective transformation. It can be applied to the calibration and surface measurement of structure light 3D reconstruction system.]]></description>
<pubDate>2021/1/26 15:57:53</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LIU Jinbo, GUO Pengyu, LI Xin]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LIU Jinbo, GUO Pengyu, LI Xin</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202101005]]></guid><cfi:id>48</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[AUV global path planning method in complex sea battle field environment]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202101006]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In view of the path planning of the unmanned AUV (autonomous underwater vehicle) in the complex sea battlefield environment, the environment model is complex and there are many constraints. A relatively perfect sea battlefield environment model including battlefield shape, enemy threats, obstacles, and sea current field was established. The AUV navigation time and threat time were the shortest as the optimization goal, and an oscillation-based type was given. The AUV global path planning method of the oscillation IWO(invasive weeds optimization) algorithm was compared with other three path planning algorithms, such as the standard IWO algorithm, the full-oscillation IWO algorithm and the PSO (particle swarm optimization) algorithm respectively. Simulation results show that the proposed method which has strong searching ability and excellent robustness, can effectively plan the navigation path which meets the performance requirements for the AUV in the complex sea battlefield environment.]]></description>
<pubDate>2021/1/26 15:57:55</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[ZHAO Miao, GAO Yongqi, WU Dixiao, WANG Peng, ZHANG Honggang]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>ZHAO Miao, GAO Yongqi, WU Dixiao, WANG Peng, ZHANG Honggang</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202101006]]></guid><cfi:id>47</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Robustness of asymmetric dependent network under cascading failure]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202101007]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[It is of great practical significance to study the robustness of networked CPS(cyber physical systems) under cascading failure. A two-tier asymmetric dependency network model was constructed for CPS with one-way dependency and a cascading failure model for asymmetric dependency network which combines the dependency failure with the overload failure was designed. A more practical asymmetric attack method was proposed, and a node capacity allocation method under resource constraints was given. Simulation experiments were carried out on asymmetric dependent networks consisting of scale-free subnets. It is found that the network robustness is positively correlated with the sub-network average, degree exponent, node capacity, etc.; assortative dependency networks and networks with node capacity allocation by degree are more robust; asymmetric dependent networks are vulnerable to attention attacks; when attacking dependent subnets with equal strength, the network is more vulnerable. The constructed model and the law of experimental discovery have certain reference value for studying network robustness and optimizing network design.]]></description>
<pubDate>2021/1/26 15:57:58</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LIU Fengzeng, XIAO Bing, LIU Junjie, WANG Haoran]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LIU Fengzeng, XIAO Bing, LIU Junjie, WANG Haoran</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202101007]]></guid><cfi:id>46</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Lightweight optimization of skinned purlin structure in launch vehicle based on sequential radial basis function]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202101008]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Taking the lightweight optimization of skinned purlin structure in large-scale launch vehicle as the research background, the post-buckling lightweight optimization of large-diameter and large-loaded skinned purlin structure was carried out. In order to achieve ultimate bearing capacity of the structure, the post-buckling behavior of skinned purlin structure was analyzed based on the parametric model established by Python code. Considering that discrete topology and continuous size variables were involved in the lightweight optimization of skinned purlin structure, sequence approximate optimization method based on the surrogate model and combinatorial optimization algorithm was proposed. What′s more, approximate optimal solution was used to accelerate algorithm convergence, which can obtain the final design scheme of skinned purlin structure. The results of engineering examples show that the sequence approximate optimization method propose in this paper make the weight loss effect of skinned purlin structure obvious, and verifies the effectiveness of the method.]]></description>
<pubDate>2021/1/26 15:57:59</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[WANG Zhixiang, OUYANG Xing, WANG Bin, ZHANG Dapeng, LEI Yongjun]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>WANG Zhixiang, OUYANG Xing, WANG Bin, ZHANG Dapeng, LEI Yongjun</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202101008]]></guid><cfi:id>45</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Variable-bandwidth design method of the random vibration environmental test condition for launch vehicle]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202206001]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[A variable-bandwidth design method based on the principle of energy equivalence was proposed for the random vibration environmental test condition of launch vehicles. By adopting the fractional octave frequency band data processing method and keeping the RMS (root mean square) in every frequency band identical with the one of the original power spectral density, the exorbitant RMS problem of the traditional constant-bandwidth random vibration environmental test condition was avoided. To validate the capability of the method, the random vibration simulations of a typical pipeline were conducted. The results indicate that the method is able to assess the product effectively rather than excessively. The proposed variable-bandwidth design method offers an efficient alternative for the conditions design in the random-vibration environment test of launch vehicles.]]></description>
<pubDate>2022/12/1 9:50:48</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[JIANG Renwei, ZENG Yaoxiang, PAN Zhongwen, LI Daokui]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>JIANG Renwei, ZENG Yaoxiang, PAN Zhongwen, LI Daokui</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202206001]]></guid><cfi:id>44</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Analysis on the failure mechanism of solid propellant under superimposed pressure]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202206002]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In the ignition state, the SRM (solid rocket motor) grain with wall pouring is in the state of superimposed pressure, while the circumferential direction of SRM inner bore is under tensile strain. It is urgent to carry out related research on the failure mechanism of propellant under superimposed pressure. The mechanical behavior of solid propellant under coupling effect of superimposed pressure, temperature and strain rate was investigated through uniaxial tensile tests at different pressure, temperature and strain rates using self-developed superimposed pressure loading system. According to the mechanical response characteristics of the propellant under superimposed pressure, the failure modes of the propellant under superimposed pressure were further studied by means of meso-scale mechanical simulation. At the same time, the morphologic sectional features of the propellant specimens were analyzed by means of scanning electron microscope test. The failure mechanism of the propellant under superimposed pressure was found out by means of combining test and simulation. The results show that the damage interfaces of propellant decrease significantly under superimposed pressure, and with the increasing of superimposed pressure, the damage form of propellant changes from particle dewetting dominated to particle breakage dominated.]]></description>
<pubDate>2022/12/1 0:00:00</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[ZHANG Liang, SHEN Zhibin, YU Kuahai]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>ZHANG Liang, SHEN Zhibin, YU Kuahai</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202206002]]></guid><cfi:id>43</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Magnus effect of electromagnetic launch hypervelocity spinning projectile]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202206003]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Compared with the traditional gunpowder bullets, electromagnetic launch bullets have the advantages of high muzzle velocity and long fire range. However, the bullet shape is no longer axisymmetric because of the armature groove at the tail, resulting in unique aerodynamic characteristics. Based on the three-dimensional unsteady Navier-Stokers equation, the aerodynamic characteristics of electromagnetic projectile were analyzed by using the sliding grid technique. Results show that for the hypervelocity spinning electromagnetic projectile, the Magnus effect comes from the interaction of shock layer distortion and the upwind area variation of the armature arm. The aerodynamic force and the moment varies periodically with the roll angle due to the periodic variation of the upwind area of the armature arm, and the Magnus moment reaches the minimum and the maximum at the roll angle of 45° and 135°, respectively. The influence of the armature arm groove is remarkable, which not only worsens the Magnus effect (increased by more than 50% at 135°), but also makes the pressure center move forward periodically (the absolute forward amount is up to 5%). Furthermore, with the increase of spinning speed, the increase of the Magnus moment and the pressure center move-forward effect become more and more significant, which is harmful to the dynamic stability of the projectile.]]></description>
<pubDate>2022/12/1 9:50:48</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LI Kai, LU Junyong, ZHANG Xiao, FENG Junhong, LI Xiangping, DU Peipei]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LI Kai, LU Junyong, ZHANG Xiao, FENG Junhong, LI Xiangping, DU Peipei</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202206003]]></guid><cfi:id>42</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Double two-body model using geometrical section method and the analysis of Earth-Moon transfer orbit from space elevator]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202206004]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Double two-body model is the fundamental conception model for solving Earth-Moon transfer orbit. The traditional approaches use the latitude and longitude of entry point on the sphere of influence to describe double two-body model, while in this paper a geometrical representation method of double two-body model by using parameters in orbital plane of flight trajectory was proposed. The search space on three-dimensional sphere was reduced to be a two-dimensional circle formed by tangent of the orbital plane and the sphere of influence, the shape parameter of Earth-Moon transfer orbit can be efficiently solved by one-parameter Brent root-finding algorithm and Lambert theory. In order to avoid double calculation, the orbital multivariate search problem calculated by the transfer orbit window was decoupled into two sub-problems, the transfer orbit shape parameter solution problem and the transfer orbital plane space orientation problem, which reduce the solution dimension of the problem, The two-stage method with parallel computing was approached in order to make full use of the nowadays computational power of multi-core computer. The simulation results show that the new parallel double two-body model with the use of geometrical section of orbital plane can be successfully applied to the analysis of the Earth-Moon transfer orbit from space elevator.]]></description>
<pubDate>2022/12/1 9:50:48</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[TONG Kewei, CHENG Binglin, WANG Xiaowei]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>TONG Kewei, CHENG Binglin, WANG Xiaowei</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202206004]]></guid><cfi:id>41</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Solar radiation intensity distribution combined with stratospheric airship flying gesture]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202206005]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The distribution of solar radiation intensity on the upper surface of the stratospheric airship is an important factor affecting the output performance of photovoltaic arrays. In order to analysis the influence of the dynamic change of the flight attitude of the stratospheric airship on its upper surface solar radiation intensity distribution characteristics and establish a calculation model of interactive coupling between the airship dynamics model and the solar radiation physical model was established. By using this mode, a certain airship example was calculated, the solar radiation intensity distribution on the upper surface of the stratospheric airship was also proposed under flight yaw and pitch angle change, and the characteristics of solar radiation intensity affected by airship flight attitude. The result can be used to guide the optimized layout and array configuration of the solar array on the stratospheric airship.]]></description>
<pubDate>2022/12/1 9:50:48</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[WANG Xuwei, LI Zhaojie, ZHANG Yanlei, WANG Yan]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>WANG Xuwei, LI Zhaojie, ZHANG Yanlei, WANG Yan</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202206005]]></guid><cfi:id>40</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Numerical and experimental study of functioning of typical linear pyrotechnic separation device]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202206006]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[At present, the optimal design of linear pyrotechnic separation device mostly depends on experiments, which is not only costly but also low efficient. Herein, a numerical model was developed with arbitrary Lagrangian-Eulerian method for a typical linear pyrotechnic separation device. The numerical model was validated via pyrotechnic separation experiments and photonic Doppler velocimetry, and it was found to have reasonable accuracy. The model was applied to study the mechanical mechanism of the transient separation process of the pyrotechnic separation device. The influence of multiple factors on the critical characteristic parameters was also studied quantitatively, such as effective plastic strain of the key areas of the device. It is found that the linear density of the detonating cord and the bottom radius of the v-notch of the separation plate have significant influence on the separation process. In addition, the material of the protection plate, the angle of the v-notch and the dimension of the rectangular notch of the separation plate also have a certain influence on the separation process, however, the influence is less than that exerted by the linear density of the detonating cord and the bottom radius of the v-notch. The study can provide a foundation for optimal design of the typical linear pyrotechnic separation device.]]></description>
<pubDate>2022/12/1 9:50:48</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[WANG Guangyu, WANG Xiaopeng, WEN Quan, WANG Yushi]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>WANG Guangyu, WANG Xiaopeng, WEN Quan, WANG Yushi</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202206006]]></guid><cfi:id>39</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Influence of lunar soil parameters on the lunar landing airbag cushioning performance]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202204008]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[To study the influence of lunar soil parameters on the airbag buffer performance, a lunar landing airbag was designed according to the landing conditions of “Chang′e 3” probe, and then an airbag dynamic model considering the characteristics of lunar soil was established based on the crushable foam model. The airbag cushioning process under different lunar soils was analyzed, and it is found that the softer the lunar soil, the smaller the payload impact acceleration, but the airbag will sink into the lunar soil, which is not conducive to venting and affects its cushioning effect. Therefore, three indicators of airbag peak pressure, payload maximum acceleration, and payload maximum drop height were used to evaluate the airbag cushioning performance comprehensively, and the influence law of lunar soil parameters was quantitatively studied. Results show that the lunar soil density and shear modulus, as well as the yield parameters a<sub>0</sub> and a<sub>1</sub>, have a significant influence on the cushioning performance, with a positive effect on the first two indicators and a negative effect on the latter one. Further research reveals that the relationship between each of the four lunar soil parameters and the three cushioning performance indicators is an exponential function.]]></description>
<pubDate>2022/7/20 0:00:00</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[ZHOU Xuan, ZHOU Shiming, LI Daokui]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>ZHOU Xuan, ZHOU Shiming, LI Daokui</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202204008]]></guid><cfi:id>38</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Method of satellite high-frequency attitude determination using compressive sampling]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202204009]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[High-frequency attitude vibration usually exceeds the measurement frequency range of spaceborne gyroscopes and star sensors,resulting in a decrease in the accuracy of satellite attitude determination. Thus,a method for high-frequency attitude determination based on the regular attitude sensors was proposed. The key idea is that the high-frequency attitude of the spacecraft was sparse in the frequency domain and can be recovered from the normal-sampling-rate measurements. In this method, the normal-sampling-rate attitude sensors and indirect Kalman filters were used to estimate attitude. The filters′ estimation results were merged, and the high-frequency attitude was recovered from the merged data using the compressive sampling algorithm. The effectiveness of the method was verified by simulation experiments.]]></description>
<pubDate>2022/7/20 0:00:00</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[WANG Pu, HU Xiangyu, AN Wei, SHENG Weidong, LIN Zaiping, ZENG Yaoyuan]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>WANG Pu, HU Xiangyu, AN Wei, SHENG Weidong, LIN Zaiping, ZENG Yaoyuan</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202204009]]></guid><cfi:id>37</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Staring control for deep space targets based on uncalibrated small video satellite]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202204010]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[A target staring adaptive attitude control method was designed, which could achieve staring at the target in the presence of the unknown target′s position and camera parameters. Based on the kinematic equation, the estimated parameters were extracted and linearized. A potential function with respect to unknown parameters was introduced to meet the demand for the rank of the parameter matrix. A self-updating principle of parameters was adopted to estimate the parameters on line, and accordingly, the adaptive control method was proposed. Based on the Lyapunov stability theory and Barbalat′s lemma, it was proved that the error between the target imaging position and the desired imaging position could asymptotically converge to zero. Simulation results reveal that the adaptive controller can effectively achieve staring observation for deep space targets with the uncertainties of the target position and the camera parameters.]]></description>
<pubDate>2022/7/20 0:00:00</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[SONG Chao, FAN Caizhi, WANG Mengmeng]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>SONG Chao, FAN Caizhi, WANG Mengmeng</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202204010]]></guid><cfi:id>36</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Roll control study of flying wing based on trailing-edge jet at wide speed range]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202204011]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The numerical simulation method was used to carry out a systematic study on the roll control of the flying wing using the trailing-edge CC(circulation control) jet at a wide speed range (Ma为0.145～0.7), and was compared with the configuration controlled by classical control surfaces. Research focuses the electromagnetic stealth characteristics, the roll control characteristics and their flow physics, and the impacts of the bleed air. Results show that as the Mach number increases, the roll control capability of the CC jet decreases due to the weakening of entrainment and blocking effects. However, the CC jet enhances the stealth performance at specific azimuth ranges remarkably. Moreover, it requires less bleed air, induces less thrust loss, and has a high control efficiency factor (aerodynamic moment coefficient produced per unit of additional drag coefficient). In conclusion,the trailing-edge CC jet is a highly promising roll control device for a flying wing.]]></description>
<pubDate>2022/7/20 0:00:00</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[SHAO Shuai, GUO Zheng, JIA Gaowei, YIN Peng, HOU Zhongxi, ZHANG Laiping]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>SHAO Shuai, GUO Zheng, JIA Gaowei, YIN Peng, HOU Zhongxi, ZHANG Laiping</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202204011]]></guid><cfi:id>35</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Multi constraint optimal intelligent gliding guidance via reinforcement learning]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202204012]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In order to improve the autonomy of gliding guidance for complex flight missions, a multi-constrained intelligent gliding guidance strategy based on optimal guidance and RL (reinforcement learning) was proposed. Three-dimensional optimal guidance was introduced to meet the terminal latitude, longitude, altitude and flight-path-angle constraints. A velocity control strategy through lateral sinusoidal maneuver was proposed, and an analytical terminal velocity prediction method considering maneuvering flight was studied. Aiming at the problem that the maneuvering amplitude in velocity control cannot be determined offline, an intelligent parameter adjustment method based on RL was studied. This method designed a state space via terminal velocity and an action space with maneuvering amplitude. In addition, it constructed a reward function that integrated the terminal velocity error and gliding guidance tasks, and used Q-Learning to achieve the intelligent adjustment of maneuvering amplitude. The simulation results show that the intelligent gliding guidance method can meet various terminal constraints with high accuracy, and can improve the autonomous decision-making ability under complex tasks effectively.]]></description>
<pubDate>2022/7/20 0:00:00</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[ZHU Jianwen, ZHAO Changjian, LI Xiaoping, BAO Weimin]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>ZHU Jianwen, ZHAO Changjian, LI Xiaoping, BAO Weimin</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202204012]]></guid><cfi:id>34</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Analysis of the application of aero engine in supersonic ejector system]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202204013]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The pressure and temperature of air flow can be increased by aero engine, so the application of aero engine in supersonic ejector system is possible. The effects of air source on ejector performance and the effects of bleeding on aero engine performance were analyzed. And 3 types of aero engine layout in supersonic ejector system were presented. According to the requirements of a supersonic ejector system, the performance parameters of all 3 types of aero engine layout were calculated. The calculation results indicate that when the pressure of the upstream gas is 0.044×10<sup>5</sup> Pa and 0.029 3×10<sup>5</sup> Pa, aero engine can directly discharge the upstream gas or be used as the driving gas source for the supersonic ejector system by reasonable selecting the engine layout and working parameters.]]></description>
<pubDate>2022/7/20 0:00:00</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[XU Dachuan, YANG Ling, SHI Yu, GU Yunsong, REN Zebin]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>XU Dachuan, YANG Ling, SHI Yu, GU Yunsong, REN Zebin</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202204013]]></guid><cfi:id>33</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Vibration reduction analysis and experiment of multi-rotor drone]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202204014]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Aiming at the problem of excessive vibration of the multi-rotor drone, which causes instability of flight state, the vibration reduction analysis work was carried out based on finite element simulation technology and experimental methods. Through frequency analysis, the reason of excessive vibration was determined to be resonance caused by coupling of natural frequency and excitation frequency,and the mode shape corresponding to the resonance frequencies were the first-order waving, the first-order swing and the second-order swing mode shapes. An optimization design method for optimizing the cross-sectional shape of the drone was proposed. Without adding extra weight, the corresponding frequency points of the first-order waving mode, the first-order swing mode, and the second-order swing mode have been increased by 37.23%, 22.47% and 18.43%, respectively. Simulation experiments prove that the proposed vibration reduction analysis and optimization design method can provide references for design work of drones.]]></description>
<pubDate>2022/7/20 0:00:00</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[MA Weili, HE Yingpeng, CUI Huiru, LI Daokui, SHEN Liulei]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>MA Weili, HE Yingpeng, CUI Huiru, LI Daokui, SHEN Liulei</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202204014]]></guid><cfi:id>32</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Spatial distribution model for behind-armor debris formed by the perforation of explosively formed projectile through target]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202204015]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The deep space impact load is of great significance to the detection of the internal material composition and structural characteristics of small celestial bodies. Therefore, based on considering the characteristics of the variable section of EFP (explosively formed projectile) and the differentiation of the BAD (behind-armor debris),a spatial distribution model for BAD formed by the perforation of variable cross-section EFP through the target was established. Under the condition that the target thickness is 30 mm to 70 mm and the EFP speed is 1 650 m/s to 1 860 m/s, the model can quantitatively predict the relationship between the velocity, mass, quantity and spatial position of each debris in the BAD cloud.The results indicate that the relative velocity increases by a linear function with the increase of the relative spatial position, the relative mass and the relative number increase by a power function with the increase of the relative spatial position.]]></description>
<pubDate>2022/7/20 0:00:00</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[XING Boyang, GUO Rui, HOU Yunhui, LUO Qiang, ZHANG Dongjiang, YANG Zhaobing, XU Weihua, ZHU Guili, CUI Hao]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>XING Boyang, GUO Rui, HOU Yunhui, LUO Qiang, ZHANG Dongjiang, YANG Zhaobing, XU Weihua, ZHU Guili, CUI Hao</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202204015]]></guid><cfi:id>31</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Effect of structural parameters of regenerative cooling channels on hydrocarbon fuel flow distribution]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202204016]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Based on the regenerative cooling technology of liquid rocket engine, the flow distribution characteristics of Z-type parallel channels were studied by numerical simulation method. The effects of channel number, channel section shape and entrance confluence structure on the flow distribution characteristics were analyzed. The results show that the non-uniformity coefficient of flow distribution decreases from 2.59% to 0.5% with the increase of the number of channels in the regenerative cooling system. Increasing the number of channels under the same flow area can effectively ensure the uniformity of flow distribution. The channel section shape has little influence on the non-uniformity coefficient of flow distribution, which is mainly reflected in the flow velocity distribution and heat transfer area in the channel, and the heat transfer effect of the trapezoidal configuration is better than that of the rectangular configuration. The entrance confluence structure is beneficial to the uniform of flow distribution. The research has a certain reference significance for the structural design of regenerative cooling channel.]]></description>
<pubDate>2022/7/20 0:00:00</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[YIN Liang, DING Jie, LIU Weiqiang]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>YIN Liang, DING Jie, LIU Weiqiang</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202204016]]></guid><cfi:id>30</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Fully implicit LU-SGS algorithms applied to stiff problems in hypersonic thermochemical non-equilibrium flows]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202202001]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In hypersonic thermochemical nonequilibrium flow calculations, a large difference between the numerical time step and the molecular vibration relaxation time or the chemical reaction time can bring about serious numerical stiffness problems, which are exacerbated by grid refinement in strong interaction areas such as near-wall or corner. The initial maximum CFL number and convergence rate are thus limited under high Reynolds conditions. The original LU-SGS algorithm only considers the implicit treatment of the source term and convection term. Two fully implicit LU-SGS algorithms, the FLU-SGS algorithm and the BLU-SGS algorithm, were developed by deriving and implementing the diagonal approximation of the spectral radius of the viscous Jacobian matrix. The convergence speeds of the three algorithms were investigated in cases of high enthalpy two-dimensional cylinder flow and axisymmetric re-entry capsule flow. The results show that strong viscous interaction and large separation can be quickly established and 3~5 orders of increase of the maximum CFL number can be reached with FLU-SGS and BLU-SGS algorithms. Thus the newly developed algorithms are efficient in accelerating convergence in the calculation of complex thermochemical non-equilibrium flows.]]></description>
<pubDate>2022/4/1 11:52:57</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[JIANG Hao, LIU Jun, WANG Junyuan, HUANG Wei, DU Yang]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>JIANG Hao, LIU Jun, WANG Junyuan, HUANG Wei, DU Yang</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202202001]]></guid><cfi:id>29</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Dynamic modeling and simulation of anti-UAV tethered-net capture system]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202202002]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Aiming at the ‘Black Fly’ problem of UAV (unmanned aerial vehicle), a program of the anti-UAV tethered-net capture system consisting of platform flying, flexible tethered-net arresting and parachute recycling was proposed, and a dynamic model of the whole process was conducted. The platform flight trajectory model and the tethered-net dynamic model were compared and verified with the test data. The results show that the proposed system dynamics modeling and simulation program is feasible and has guiding significance for engineering system design.]]></description>
<pubDate>2022/4/1 11:52:57</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[CHEN Qingquan, FENG Zhiwei, ZHANG Guobin, WANG Xing, ZHANG Qingbin]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>CHEN Qingquan, FENG Zhiwei, ZHANG Guobin, WANG Xing, ZHANG Qingbin</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202202002]]></guid><cfi:id>28</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Nonlinear thermal flutter characteristics of thermoplastic composite panels in supersonic flow]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202202003]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The flutter behavior of thermoplastic composite structures in high-speed flow is a key problem in the design of reusable spacecraft. Based on the classical Mindlin thick theory, the Von-Karman larger deformation theory and the piston theory, the thermoplastic composite structure panel and its aerodynamics were described, along with the consideration of both the thermal stress and the variation of mechanical properties caused by the temperature. The aeroelastic model of the thermoplastic composite panel was established based on the principle of virtual work and the finite element method,and the V-g method and the Newmark method were used to solve the thermal flutter characteristics of the thermoplastic panel from frequency domain and time domain, respectively. After the validity and convergence of the presented method were verified, the effects of temperature on mode coupling in frequency domain, limit cycle oscillation in time-domain and stress response were investigated.The results show that the flutter dynamic pressure obtained by considering the temperature variation of thermoplastic materials will further reduce the flutter dynamic pressure of the panel, and the equivalent stress of thermoplastic panels under the limit cycle oscillation is lower than the material yield limit.]]></description>
<pubDate>2022/4/1 11:52:57</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[GAO Yihang, DUAN Jingbo, LEI Yongjun]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>GAO Yihang, DUAN Jingbo, LEI Yongjun</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202202003]]></guid><cfi:id>27</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Elastic-plastic analysis for thermoplastic composite cantilever beams by bending moment]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202202004]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Based on the Timoshenko beam theory and the Tsai-Hill yield criterion, a mathematical model for elastic-plastic analysis for cantilever beams by bending moment was established. Meanwhile, the analytical solutions of stress and displacement were obtained. The solutions were verified in comparison with the ones available in the literature and finite element. Furthermore, the effects of fiber orientation angle, bending moment, aspect ratio and fiber volume fraction on the elastic-plastic stress and displacement of the beam were examined in detail. The results can provide important references for the design and engineering applications of thermoplastic composites.]]></description>
<pubDate>2022/4/1 11:52:57</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LEI Yongjun, LIU Mingwei, ZHANG Dapeng, GAO Yihang]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LEI Yongjun, LIU Mingwei, ZHANG Dapeng, GAO Yihang</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202202004]]></guid><cfi:id>26</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Tonal noise prediction of interaction between stator and rotor of subsonic axial fan]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202202005]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The tonal noise, radiated by interaction between stator and rotor, is the main noise source of the subsonic axial fan. A rapid method to predict the noise is significant to the parameter design in early stage of the fan low radiation noise design. Therefore, a semi-analytic prediction formula of the power of radiated tonal noise of the interaction between stator rotor cascade was derived, by considering the interaction of stator and rotor blades based on the cascades response function theory, and by simulating the rotor wakes using empirical rotor wake model. The applicability of the formula was verified by comparing with the results of the existing experimental model and computational model from NASA. Based on NASA experiment model, the effect of rotor-stator spacing and stator blade parameters on tonal noise of fan was analyzed further. And the results show that increase of the rotor-stator spacing and lean design of stator blades suppresses the tonal noise caused by the interaction between stator and rotor effectively .]]></description>
<pubDate>2022/4/1 11:52:57</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[WU Xingyu, WEI Yingsan, JIN Shuanbao, WANG Dong, ZHU Hao, HU Pengfei, SUN Fangxu]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>WU Xingyu, WEI Yingsan, JIN Shuanbao, WANG Dong, ZHU Hao, HU Pengfei, SUN Fangxu</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202202005]]></guid><cfi:id>25</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Applying the method of normal forms to projectile nonlinear motion analysis]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202202006]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Nonlinearity especially from aerodynamic coefficients in high orders has a significant effect on projectile dynamics. Its investigation has been hindered in the conventional analysis by the complexity in nonlinear motion equations and the lack of appropriate analysis tools. Therefore, the widely used method of normal forms was introduced for the analysis of projectile angular motion. Considering the second order damping and the seventh order static moment terms, the normal form of the angular motion was derived and thus the universal analytical solution of the angle of attack is obtained, which is verified to show good agreement with the numerical integration results over a wide range of angle of attack and also demonstrates its being applicable to the undamped case and the cases with lower or higher order of static moment. In addition, the obtained relationship between initial conditions can give a conventional but simple determination of the region of attraction to the origin. Also, the amplitude equation combined with the equilibrium analysis provides a accurate prediction for the existence and stability of limit cycle in angular motion.]]></description>
<pubDate>2022/4/1 11:52:57</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LI Dongyang, CHANG Sijiang, WANG Zhongyuan, WEI Wei]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LI Dongyang, CHANG Sijiang, WANG Zhongyuan, WEI Wei</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202202006]]></guid><cfi:id>24</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Mesh parameterization in reliability-based design optimization for the life of turbine blade with film holes]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202202007]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In order to meet the RBDO (reliability-based design optimization) requirement for the life of turbine blade with film holes by automatic programmed control, the local parameterization method was proposed on the basis of the unstructured mesh, which significantly reduces the time costs of FEA (finite element analysis). The turbine blade was separated into two regions:the parameterized region and the non-parameterized region. After the meshes of the non-parameterized region and control points of the parameterized region were completed, only the meshes of parameterized region were required to be reconstructed when the geometry of film holes was updated. Compared with the global deformation method based on the structured mesh, the proposed method dramatically reduces the time costs of FEA while ensuring the accuracy of finite element calculation, which highly improves the efficiency of RBDO.]]></description>
<pubDate>2022/4/1 11:52:57</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[LEI Jingyu, LYU Zhenzhou, JIA Beixi]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LEI Jingyu, LYU Zhenzhou, JIA Beixi</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202202007]]></guid><cfi:id>23</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Structural integrity analysis of bonding interface of vertical storage motor based on axisymmetric cohesive element]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202202008]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The establishment of axisymmetric cohesive force element is an important method to conduct stress analysis of the bonding interface of vertical storage motor. The reference coordinate system was established on the deformed axisymmetric cohesive force element, and the transformation relationship between elemental node displacement in the reference coordinate system and the global coordinate system was derived. The internal force vector and the stiffness matrix of the element were derived based on the elemental separation displacement. The separation test of the axisymmetric bonding plate was carried out to verify the accuracy and efficiency of the axisymmetric cohesive force element. The structural analysis of solid rocket motor in vertical storage under axial acceleration and wave load has been carried out successively, and the magnitude and the distribution pattern of stress at the bonding interface have been studied emphatically. The research method and its conclusion can provide a useful reference for the structural analysis of bonding interface of solid rocket motor.]]></description>
<pubDate>2022/4/1 11:52:57</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[WANG Junqi, BAO Futing, CUI Huiru]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>WANG Junqi, BAO Futing, CUI Huiru</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202202008]]></guid><cfi:id>22</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Position and attitude estimation algorithm and error analysis of high-spin projectile based on dual high-speed cameras intersected]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202202009]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In order to measure the various information of the high-rotation projectile at the muzzle, a new method for estimating the position and attitude of projectiles based on the intersection of dual high-speed cameras was proposed. The error modeling and analysis of the total angle of attack function were carried out. Results show that the optical axes of the two cameras should be perpendicular to each other, and the measurement function of the camera with the optical axis far from the plane of attack should be selected to calculate the total angle of attack. Under this circumstance, the measurement error is the smallest. The conclusion of error analysis and the position and attitude estimation algorithm was verified by the shooting range experiments. Experimental results show that the conclusions of error analysis are correct, and the proposed position and attitude estimation algorithm is not based on any assumptions and its accuracy is higher than that of the POSIT(pose from orthography and scaling with iteration) algorithm. The initial velocity measurement error does not exceed 0.6 m/s, and the projectile centroid position measurement error does not exceed 0.3 m. The measurement method is a non-contact measurement and easy to implement. More importantly, the measurement information is comprehensive. So it can provide a reference basis for shooting range experiments, acceptance and other works.]]></description>
<pubDate>2022/4/1 11:52:57</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[YANG Zhiwei, WANG Liangming, ZHANG Xifeng, WANG Yao]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>YANG Zhiwei, WANG Liangming, ZHANG Xifeng, WANG Yao</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202202009]]></guid><cfi:id>21</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Compensation method of parachute deployment load based on recurrent neural networks]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202202010]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Focusing on predicting the parachute deployment load in the process of inflation accurately, a compensation calculation method of parachute deployment load with RNN (recurrent neural networks) was proposed, including the model architecture and data processing. The predicted value calculated by inflation time method was brought into the RNN for the secondary calculation, so that the final result could be close to the airdrop experiment data. The feedforward neural networks, standard recurrent networks and long short-term memory networks were used to compare the model characteristic. The research verified the applicability and accuracy of the prediction results and analyzed the effects of hyperparameters such as learning rate, input layer dimension and hidden layer dimension on the performance. The optimal training condition for reference to the compensation model was developed through the test. The results show that the utilization of RNN for parachute deployment load prediction is effective and provides a referential significance for the interdisciplinary research of machine learning and parachute industry.]]></description>
<pubDate>2022/4/1 11:52:57</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[JIANG Tian, LI Jian, GE Sicheng]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>JIANG Tian, LI Jian, GE Sicheng</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202202010]]></guid><cfi:id>20</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Research progress of anti-irradiation MRAM]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202306019]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The novel non-volatile MRAM(magnetic random access memory) has the advantages of fast read and write speed, long data retention time and low power consumption, which attracts wide attention from researchers. Its excellent anti-irradiation capabilities are explored in depth, and further applications in aerospace and other fields are expected. The industrial development, technological changes and applications of MRAM were reviewed, the mature MRAM products of recent years were listed, and the advantages and disadvantages of different generations of MRAM were analyzed. The radiation effects of MTJ(magnetic tunnel junction) and read/write circuit based CMOS(complementary metal oxide semiconductor) were discussed. The recent achievements in anti-radiative hardening design for MRAM were summarized. The development prospect of anti-irradiation MRAM in aerospace field and even nuclear energy field was prospected.]]></description>
<pubDate>2024/11/27 0:00:00</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[SUN Jiejie,WANG Chao,LI Jiawei,JIANG Chuanpeng,CAO Kaihua,SHI Hui,ZHANG Youguang,ZHAO Weisheng]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>SUN Jiejie,WANG Chao,LI Jiawei,JIANG Chuanpeng,CAO Kaihua,SHI Hui,ZHANG Youguang,ZHAO Weisheng</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202306019]]></guid><cfi:id>19</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Modeling and numerical simulation of constant-height flight by air-lifting gas mixing for aerostats]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202306020]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[According to the floating weight balance characteristics and the ideal gas state equation, a method to control the height of the aerostat′s flat flight by gas mixing was explored, and the overall design research of constant-height flight by air-lifting gas mixing was carried out. Considering the importance of thermodynamic characteristics to the ascent process and the flat flight process of the aerostat, combined with the thermophysical properties of mixed gas in engineering thermodynamics, the super-pressure balloon was taken as the research object to analyze the thermal environment during the ascent and flight processes of spheres, and coupled with dynamic models. On this basis, the mechanical simulation of the ascent and flat flight process of the balloon was carried out, and the changes in altitude, speed, gas temperature and pressure during the ascent of the balloon were obtained, so as to verify the feasibility of the theoretical model of constant-height flight by air-lifting gas mixing, and provide guidance for the subsequent aerostat flight test.]]></description>
<pubDate>2024/11/27 0:00:00</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[YANG Yanchu,CAO Shenghong,ZHAO Rong,ZHU Rongchen,SONG Lin]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>YANG Yanchu,CAO Shenghong,ZHAO Rong,ZHU Rongchen,SONG Lin</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202306020]]></guid><cfi:id>18</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Cascade control strategy for depth tracking of supercavitating vehicle]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202306021]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[To enhance the stability of the supercavitating vehicle caused by the nonlinear planing force between the cavitation and the vehicle, a cascade control method for the depth tracking was proposed based on the circle criterion theory and the Nelder-Mead algorithm. The mathematical model of the supercavitating vehicle and the circle criterion theorem were introduced. The cascade error state equation of the supercavitating vehicle was established based on the model, and the absolute stability of the inner-loop was studied using the circle criterion. The inner-loop feedback parameters were further optimized through the Nelder-Mead algorithm. The simulation analysis results show that the control method proposed in this paper is convenient for feedback parameter tuning, and can realize the accurate depth tracking effectively.]]></description>
<pubDate>2024/11/27 0:00:00</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[SUN Mingwei,ZHOU Yu,ZHANG Jianhong,CHEN Zengqiang]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>SUN Mingwei,ZHOU Yu,ZHANG Jianhong,CHEN Zengqiang</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202306021]]></guid><cfi:id>17</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Analysis of flow field characteristics of S-bend inlet with dual synthetic jets]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202306022]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[S-bend inlet leads to obvious flow separation and apparent total pressure distortion in unmanned aerial vehicle. To solve this problems, an active flow control method based on dual synthetic jets was proposed accordingly. The numerical simulation model of S-bend inlet with dual synthetic jets was established. The results show that dual synthetic jets can effectively suppress the boundary layer flow separation near the separation point of S-bend inlet through "blowing" and "suctioning" in the whole jet cycle, and effectively improve the total pressure recovery coefficient. The effects of different jet angles, jet peak velocities and jet frequencies on the flow field control characteristics of S-bend inlet were studied. The results shows that the smaller the angle between the dual synthetic jet and the main stream is, the better the flow separation control effect will be. The larger jet peak velocity will form a "blocking" effect on the main stream, resulting in a decrease in control effect. The closer the jet frequency is to the characteristic frequency of the flow field, the more obvious the control effect will be.]]></description>
<pubDate>2024/11/27 0:00:00</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[PENG Wenqiang,LUO Zhenbing,ZHOU Xinrun,ZHU Yinxin,ZHOU Yan]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>PENG Wenqiang,LUO Zhenbing,ZHOU Xinrun,ZHU Yinxin,ZHOU Yan</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202306022]]></guid><cfi:id>16</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Analysis of the current research on the flying-wing aircraft]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202403005]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The development trajectory of the flying-wing aircraft was sorted out, encompassing the early evolutionary history to the current state of research, along with contemplation and forecasts regarding future directions. Meanwhile, several key control challenges associated with flying-wing aircraft were discussed, including attitude control in a wide-speed domain under nonlinear conditions, high-precision autonomous take off and landing control under multiple effect coupling, robust control issues with approximate aerodynamic models and under strong disturbances, as well as control allocation problems arising from multi-surface redundancy. Moreover, the discussion on flow control issues that were currently a focal point in flying-wing aircraft research were discussed in depth. The following research trend of active flow control technology was expounded.]]></description>
<pubDate>2024/6/18 0:00:00</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[CHEN Qingyang, XIN Hongbo, WANG Peng, ZHU Bingjie, WANG Yujie, LU Yafei]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>CHEN Qingyang, XIN Hongbo, WANG Peng, ZHU Bingjie, WANG Yujie, LU Yafei</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202403005]]></guid><cfi:id>15</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Dynamic response analysis of rocket connection structure considering discrepancy of bolt preloads]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202403006]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In order to address the problem that the dynamic response characteristics of the bolted flange connection structure, which is widely used in aerospace rocket structures, are significantly affected by the magnitude of bolt preload, the static and dynamic response characteristics of the rocket connection structure were studied taking into account the discrepancy of bolt preloads under different conditions. A set of methods for analyzing the dynamic response of rocket body connection structures considering the discrepancy of bolt preloads was proposed based on finite element analysis and knock tests for a specific barrel-shell bolted flange connection structure. By investigating the response characteristics of the connection structure with a loose bolt, a new bolt loosening detection procedure based on the complementary ensemble empirical mode decomposition algorithm is proposed which can quantify the characteristics of the increase of the frequency response amplitude in the middle and high frequency bands of the connection structure when the loosening happens, and can quickly identify the occurrence of loose conditions without damage.]]></description>
<pubDate>2024/6/18 10:27:57</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[SUN Weicheng, GUAN Zhenqun, PAN Jiacheng, ZENG Yan 〖JZ]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>SUN Weicheng, GUAN Zhenqun, PAN Jiacheng, ZENG Yan 〖JZ</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202403006]]></guid><cfi:id>14</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Bending and buckling behavior analysis of the carbon nanotubes reinforced composites Timoshenko beams]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202403007]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Bending and buckling behavior of the macro CNTRCs (carbon nanotubes reinforced composites) beam was studied considering the scale effect of CNTs (carbon nanotubes). Based on the EMT (Eshelby-Mori-Tanaka) method and using nonlocal theory to characterize the scale effect of CNTs, the nonlocal EMT constitutive model was established. According to the Timoshenko beam theory, the static differential equations and boundary conditions of CNTRCs beams were derived through Hamilton principle. Bending response and ultimate buckling load of CNTRCs beams at S-S (simply supported) edges were obtained and compared with the literature to verify the correctness of the proposed model and solution method. Influences of the scale effect parameters and volume fraction of CNTs and the slenderness ratio of composite beams on the bending response and ultimate buckling load of S-S CNTRCs beams were analyzed. Results show that the equivalent stiffness of the CNTRCs beam is weakened by considering the scale effect of CNTs, and the volume fraction of CNTs and the scale effect parameter both have a great impact on the bending response and ultimate buckling load of the CNTRCs beam with a large slenderness ratio.]]></description>
<pubDate>2024/6/18 0:00:00</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[WU Dong, ZHANG Dapeng, YU Baoshi, LEI Yongjun]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>WU Dong, ZHANG Dapeng, YU Baoshi, LEI Yongjun</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202403007]]></guid><cfi:id>13</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Chemical nonequilibrium simulation analysis of inflatable reentry decelerator]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202403008]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The aerodynamic characteristics of the inflatable reentry decelerator were studied with chemical nonequilibrium numerical simulation using five-species air model. The effects of reentry decelerator′s shape deformation on distributions of flow temperature and pressure , heat flux and pressure along the wall were investigated, and the mole fractions of each species in the flow filed were presented. The modeling results show that the shape deformation of inflatable reentry decelerator has little influence on flow characteristic, and leads an increase of heat flux on the capsule surface. The study of species distribution shows that since N<sub>2</sub> is more difficult to dissociate than O<sub>2</sub>, the mole fraction of N is much lower than the mole fraction of O in the flow filed. Under the current calculation conditions, the ration of nitrogen and oxygen along the wall and axis is almost consistent with the incoming flow. The modeling study results are in good agreement with the experiment results, which verify the reliability of the model.]]></description>
<pubDate>2024/6/18 10:27:57</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[HE Qingsong, WANG Guangxing, FENG Rui, DONG Haibo, HUANG Mingxing, JIA He]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>HE Qingsong, WANG Guangxing, FENG Rui, DONG Haibo, HUANG Mingxing, JIA He</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202403008]]></guid><cfi:id>12</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Preferred plane bank-to-wind technology for plane-symmetric launch vehicle]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202403009]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The control force can be mismatched on pitch and yaw plane for plane-symmetric launch vehicle, a control method named BTW(bank-to-wind) was proposed to solve the problem, which adjusts the windward side according to rolling program angle to decrease the maximum engine deflection. The off-line method of BTW control was studied, the analytical solution of the theoretical value of BTW control rolling program angle was derived, and it was proved that the deviation of the theoretical value is the same order as the flight attitude deviation. A fitting algorithm based on Fourier series with weights was proposed to modify the rolling program angle, ensuring engineering feasibility. Six-degree-of-freedom flight dynamics simulations were conducted to analyze the impact of BTW control on control forces, aerodynamic loads, and the tracking quality of the program angle, thereby verifying the effectiveness of BTW control. By comparing the simulation results of different fitting base frequencies, it is concluded that excessively high fitting frequencies can affect control quality. From an engineering perspective, the "smoothness" of the rolling program angle is more important than its "fitting accuracy".]]></description>
<pubDate>2024/6/18 10:27:57</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[ZHAO Yongzhi, ZHANG Puzhuo, DU Haoyu, TANG Pan, WANG Ziyang]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>ZHAO Yongzhi, ZHANG Puzhuo, DU Haoyu, TANG Pan, WANG Ziyang</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202403009]]></guid><cfi:id>11</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Wall boundary condition for the R13/R26 moment method at mesoscopic level]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202403010]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Wall boundary conditions for the macroscopic equations, i.e. the NSF(Navier-Stokes-Fourier) equations, R13/R26 moment equations, lose their accuracy dramatically and are easy to diverge, especially in the middle and high Knudsen number regimes.To overcome these difficulties, a wall boundary condition for the R13/R26 moment method was proposed at the mesoscopic level. The velocity distribution function was reconstructed and feedback into the Boltzmann model equation in the near-wall region, and the wall boundary condition for the R13/R26 moment method was calculated on the basis of solving the Boltzmann equation with the discrete velocity method. Results indicate that:the proposed wall boundary condition is able to increase the computational accuracy up to 59.84% compared with the classical approach. Meanwhile, it is able to get the steady-state solution for the Knudsen number up to 1.0.]]></description>
<pubDate>2024/6/18 10:27:57</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[YANG Weiqi, YANG Hui]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>YANG Weiqi, YANG Hui</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202403010]]></guid><cfi:id>10</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Development and verification of shape memory alloy self-resetting vibration damping device]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202403011]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In order to improve the flow induced vibration of the adjustable central flap mechanism deployed in the second throat in the working state, a SMA (shape memory alloy) self-resetting vibration damping device which could meet the limited installation space of the central flap mechanism was designed and manufactured according to the biasing two-way driving principle of SMA. The SMA constitutive relation subroutine compiled by UMAT interface was used to realize the numerical analysis of the maximum pressing force of the damping device, and the error between the numerical analysis and the static test results is about 2.58%. A ground vibration reduction test platform was built to test the vibration reduction effect of SMA self-resetting vibration damping device in the separated and closed states. The vibration reduction test results show that the vibration response of the central flap mechanism is significantly reduced with SMA self-resetting damping device activated. An obvious damping effect appear in the frequency band of 0～100 Hz, especially, the damping rate in the range of low frequency to 55 Hz is greater than 50%.]]></description>
<pubDate>2024/6/18 10:27:57</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[MA Yueyin, LI Daokui, NIE Xutao, ZHANG Wei, GAO Xinyu, CHEN Wanhua, CHEN Zhenhua]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>MA Yueyin, LI Daokui, NIE Xutao, ZHANG Wei, GAO Xinyu, CHEN Wanhua, CHEN Zhenhua</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202403011]]></guid><cfi:id>9</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Adaptive control techniques in the shock wave/turbulence boundary layer interaction]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202402005]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Starting from the mechanism of SWTBLI(shock wave/turbulent boundary layer interaction) and the urgent need for flow control, the research progress of the adaptive control techniques in the SWTBLI from four aspects was summarized, namely adaptive vortex generator, adaptive bump, adaptive micro jets and adaptive secondary recirculation jet. Analysis shows that developing adaptive flow control techniques, combined with AI technology, and accelerating intelligent control schemes can be used as an important technical means for wide-speed flight of the new generation hypersonic vehicle. Specifically, it is to realize local flow acceleration/deceleration, aerodynamic thermal protection, aerodynamic control and other functions in different areas of the hypersonic vehicle by adjusting external excitation, and to establish a control feedback loop according to flow field parameters, so it can adaptively adjust the structure of the local flow field to meet the actual needs of engineering.]]></description>
<pubDate>2024/4/7 0:00:00</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[HUANG Wei, WU Han, ZHONG Xiangyu, DU Zhaobo, LIU Jun]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>HUANG Wei, WU Han, ZHONG Xiangyu, DU Zhaobo, LIU Jun</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202402005]]></guid><cfi:id>8</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Sequential truncated probability circle test for hit accuracy of missile]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202402006]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[For the calculation difficulty directly of the circular error probability test, a truncated sequential probability circle test method was proposed. Taking the target point as the center, two concentric circles were drawn, in which the area within the small circle was the acceptance domain, the area outside the big circle was the rejection domain, and the middle area was the continuing test domain. On this basis, the basic decision rules in sequential testing were defined, and a calculation model for the risk of both parties and the average number of experiments was provided. Two different decision threshold optimization calculation models were proposed, and the acceptance and rejection domain radii were determined by solving the optimization problem. The various parameters in the inspection scheme under two different decision threshold calculation methods were analyzed using numerical simulation. Among them, the calculation model with the minimum average number of experiments as the optimization objective has better engineering practicality.]]></description>
<pubDate>2024/4/7 0:00:00</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[YANG Huabo, ZHANG Shifeng]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>YANG Huabo, ZHANG Shifeng</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202402006]]></guid><cfi:id>7</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Acceleration scheme for the mesoscopic numerical simulation in the kinetic theory of rarefied gas]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202402007]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[To overcome the difficulty that DVM(discrete velocity method) for solving the Boltzmann equation has extremely slow convergence speed and high computational resource consumption in the slip flow and early transition flow regimes, an acceleration scheme which coupling the mesoscopic/macroscopic equations in the full flow area was proposed. Boltzmann model equation could be solved based on the DVM using finite difference method at the mesoscopic level, and the moment equations could be solved based on the semi-implicit method for pressure linked equations using finite volume method at the macroscopic level. Fast convergence characteristic of the Navier-Stokes-Fourier/R26 moment equations in the low Knudsen number regime was fully utilized to accelerate mesoscopic equation. The distribute function could be reconstructed from the high-order Hermite polynomial function, so that the data transfer between the macroscopic and the mesoscopic equations could be done. Simulation results indicate that:the acceleration scheme, coupling the mesoscopic/macroscopic equations in the full flow area, shows great acceleration performance in the slip and early transition regime, which is able to save up to 95.28% computational time cost. However, the acceleration performance decreases significantly in the middle and large Knudsen number regime.]]></description>
<pubDate>2024/4/7 0:00:00</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[YANG Weiqi]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>YANG Weiqi</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202402007]]></guid><cfi:id>6</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Suppression of nonlinear flutter for a wing with freeplay of high speed aircraft using nonlinear energy sink]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202402008]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The subcritical problem of wing flutter system with freeplay nonlinearity was addressed by introducing the NES(nonlinear energy sink) technology to improve the critical velocity of the system′s limit cycle oscillation. A dynamic model of flutter system with NES control for wings with freeplay nonlinearity was established, and the suppression effects of NES parameters such as mass ratio, frequency ratio, damping ratio, and relative position on the limit cycle oscillation of the flutter system were analyzed. The influence of NES parameters on the critical speed of the limit cycle oscillation of the flutter system was also investigated. The results show that a larger damping ratio can stabilize the system at a smaller natural frequency ratio but required a more stringent location requirement for the NES, i.e., closer to the leading edge of the wing. On the other hand, a smaller damping ratio results in a smaller NES mass required to stabilize the limit cycle response of the flutter system. When the NES location is closer to the leading edge of the wing, increasing the natural frequency ratio significantly improve the suppression effect of limit cycle oscillation, and increasing the mass ratio also significantly improve the suppression effect and critical speed of limit cycle oscillation. Additionally, a smaller damping ratio of the NES results in better suppression of limit cycle oscillation in the flutter system.]]></description>
<pubDate>2024/4/7 0:00:00</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[NIU Yaobin, WANG Zhongwei, HUANG Wei]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>NIU Yaobin, WANG Zhongwei, HUANG Wei</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202402008]]></guid><cfi:id>5</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Effect of combustor leading edge expansion angle on rotating detonation ramjet]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202402009]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[A series of direct-connected tests were conducted on a rotating detonation ramjet with a cylindrical isolator-combustor configuration, under the conditions of a total temperature of 860 K and <i>Ma</i>=2 inflow. The influence of the combustor leading edge expansion angle(<i>θ</i>=30°,45°,60°, 90°) on the propagation characteristics, operating range, and pressure distribution of detonation waves was investigated. The results indicate that the combustion mode is consistently deflagration when the expansion angle of the leading edge of the combustor is 90°. As the expansion angle gradually decreases, the combustion mode transitions towards sawtooth and hybrid mode (including single wave stage). When the expansion angle of the leading edge of the combustor is 30°, the rotating detonation exhibits the widest self-sustaining operating range and highest combustor pressure. Additionally, as the expansion angle decreases, the lower limit of the equivalence ratio for achieving the hybrid mode decreases. At the same time, the impact of combustion modes on the inflow was analyzed and it was found that the periodic high-frequency pressure oscillation in the sawtooth wave/hybrid mode combustor could cause the positioning of leading edge of the shock train in the isolator to move upstream. The hybrid mode has the most significant impact on supersonic inflow.]]></description>
<pubDate>2024/4/7 0:00:00</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[WANG Guangyu, LIU Weidong, 刘世杰, PENG Haoyang, ZHANG Hailong]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>WANG Guangyu, LIU Weidong, 刘世杰, PENG Haoyang, ZHANG Hailong</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202402009]]></guid><cfi:id>4</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Reinforcement learning of ballistic maneuver adjustment strategy after missile penetration]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202402010]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In order to solve the problem of trajectory maneuver adjustment caused by large deviation of flight trajectory after midcourse penetration of ballistic missile, an optimization model of maneuver adjustment timing strategy was established. A reverse sequence <i>Q</i> learning algorithm for maneuver adjustment was designed, and a Tile coding approximator encoding was used to encode the state characteristics space, and the space was linearly approximated. A reverse-order update strategy mechanism combining <i>Q</i> learning algorithm and Monte Carlo method was constructed, the optimal timing of missile maneuvering adjustment was trained. The simulation results show that the strategy obtained by training 10 000 generations of reinforcement learning algorithm can reliably control the adjustment decision of flight trajectory after missile penetration with the minimum maneuver times under given scenario parameters, which verifies the effectiveness of the method.]]></description>
<pubDate>2024/4/7 0:00:00</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[FAN Boxuan, CHEN Guiming, HAN Lei, LI Bing]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>FAN Boxuan, CHEN Guiming, HAN Lei, LI Bing</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202402010]]></guid><cfi:id>3</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Optimal design for the high-speed and lightweight transmission system of SpaceFibre node]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202402011]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[An optimal design of SpaceFibre node transmission system was proposed to meet the high bandwidth, high reliability and light weight requirements for the SpaceFiber link between satellite payloads. This design adopts an incremental calculation method based on frame accumulation to reduce the redundancy of computing circuits, and satisfies the timing requirements for error detection operations through a four-stage pipeline architecture. The module balances the use of hardware resources by sharing CRC(cyclic redundancy check). To improve reliability, the design adopts a two-layer control strategy with complete response. Resource-optimized FSM(finite-state machine) and storage architecture are built to simplify the implementation of the retransmission algorithm. A verification system at board-level with two nodes was implemented in XC7Z100FFG900-2 FPGA(field programmable gate array). The results show that the design satisfies the functions stipulated by the standard. Compared with similar design schemes, the maximum frequency is increased by 1.5 times, and supports up to 6.25 Gbit/s transmission rate. And resources of lookup tables and storage are reduced, while register resources are similar. The design provides a reference for the development of high-speed and reliable SpaceFibre codecs with independent intellectual property rights.]]></description>
<pubDate>2024/4/7 0:00:00</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[ZHENG Jingya, AN Junshe]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>ZHENG Jingya, AN Junshe</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202402011]]></guid><cfi:id>2</cfi:id><cfi:read>true</cfi:read></item>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Fast incremental one-class support vector machine algorithm for rocket engine fault detection]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202402012]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In order to solve the problem of imbalance between positive and negative samples in liquid rocket engine fault diagnosis, and to enable adaptive fault detection during engine steady working state, a anomaly detection model based on fast incremental one-class support vector machine was established. Feature engineering method was adopted to extract features from sensor-obtained multivariate time series. Through incremental leaning, the one-class support vector machine model was improved and applied to liquid rocket engine anomaly detection. The one-class support vector machine detection model was endowed with adaptability for various engine individuals and multiple working conditions, while increasing computing speed. The analysis results of multiple hot test data show that the model is effective, fast-training and practically valuable.]]></description>
<pubDate>2024/4/7 0:00:00</pubDate>
<category><![CDATA[航天工程]]></category>
<author><![CDATA[ZHANG Wanxuan, ZHANG Jian, LU Zhe, XUE Wei, 张楠]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>ZHANG Wanxuan, ZHANG Jian, LU Zhe, XUE Wei, 张楠</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202402012]]></guid><cfi:id>1</cfi:id><cfi:read>true</cfi:read></item>
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