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<title cf:type="text"><![CDATA[Editorial department of the Journal of National University of Defense Technology -->航天工程·控制科学与工程]]></title>
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<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Development of hot gap measurement system for the ion thruster optics]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202001008]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In order to complete the high-precision measurement of the LIPS-300 ion thruster hot gap in the vacuum, high-temperature environment, a non-contact videometrics system using a telemicroscope was designed. Based on the captured image, the interactive partitioning edge detection method was used to obtain stable and clear edges of multiple circular cooperation logos, meanwhile the magnification factor calibration, image distortion correction, horizontal plane correction and hot gap subpixel level deformation detection were performed with cooperation logos. The accuracy verification experiments show that the measurement accuracy of the system is better than 6 μm under non-heating conditions, and the measurement accuracy is better than 12 μm under heating conditions. Experimental results show that the greater the temperature difference between the screen and the accelerator grid, the larger the reduction of the grid hot gap, when the screen grid and the accelerator grid temperature difference is at most 150 ℃, and the hot gap reduction reaches a maximum of 420 μm. At the same time, due to the thermal deformation of the mounting ring, the thermal deformation of the grid decreases during thermal steady state, and the negative displacement occurs during the cooling period. The results of grid thermal deformation measurements are consistent with the trend of similar previous experiments, and the system meets the requirements of ion thruster hot gap measurement.]]></description>
<pubDate>2020/1/19 17:05:07</pubDate>
<category><![CDATA[航天工程·控制科学与工程]]></category>
<author><![CDATA[YUAN Jiehong, LIANG Dong, ZHOU Shiming, XIAO Shijie, LI Xingkun, YANG Juntai]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>YUAN Jiehong, LIANG Dong, ZHOU Shiming, XIAO Shijie, LI Xingkun, YANG Juntai</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202001008]]></guid><cfi:id>10</cfi:id><cfi:read>true</cfi:read></item>
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<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Algorithm of single-satellite localization from frequency measurements combining initial value calibration and second order approximation]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202001009]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In order to reduce the error of single-satellite localization from frequency measurements, an algorithm of single-satellite localization from frequency measurements, which combines the initial value calibration and the second order approximation, was proposed. The algorithm obtains distance information from the satellite to the localization target at the time point when the Doppler frequency shift of the satellite receiving signal is zero, and then corrects the geometric relationship between the orbit plane and the localization target by using the distance information, thus it provides a calibration method for the selection of the initial value. By substituting the calibrated initial value into Taylor′s expansion of the localization equation containing the second order numbers, the real position of the localization target was obtained through fewer number of iteration, thus reducing the complexity of localization algorithm and improving the localization accuracy. The simulation results indicate that compared with the Doppler single-satellite localization algorithm, the iteration times and the localization error of the proposed algorithm are reduced substantially. The algorithm is easy to implement, low in computation and small in error, and has high theoretical and practical value in the field of single-satellite localization research.]]></description>
<pubDate>2020/1/19 17:05:07</pubDate>
<category><![CDATA[航天工程·控制科学与工程]]></category>
<author><![CDATA[ZHANG Jinyi, WANG Bin, QIN Fen, ZHU Hongtao]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>ZHANG Jinyi, WANG Bin, QIN Fen, ZHU Hongtao</atom:name>
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<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202001009]]></guid><cfi:id>9</cfi:id><cfi:read>true</cfi:read></item>
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<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Reentry tracking control of hypersonic vehicle with fly zone constraints]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202001010]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In order to establish the accurate reentry model of hypersonic vehicle, the aerodynamic parameters of the dynamic equation were fitted according to NASA′ s research data. Based on the physical properties and the practical application of the aircraft material, the constraints of heat flow, overload, dynamic pressure and fly zone constraints were set up, and the nonlinear multi-coupling optimal control problem was formed. The hp-adaptive pseudospectral method was used to transform the model. Through the mesh refinement process, the time interval of the larger change of state was further subdivided, and the optimal trajectory of the condition was calculated by using the SNOPT solver solution. A closed loop controller was designed to track the trajectory changes of the optimal trajectory, and to test the performance of the system and to evaluate it. The simulation results showed that during the whole reentry process, the speed decline process of the aircraft is stationary, the reentry trajectory can satisfy the constraint conditions, and the maximum transverse range is obtained while avoiding the no flight area. The angular velocity of the three channels is convergent and controllable, and the tracking of the attitudes is ideal. Above all, the controller can basically adjust the posture.]]></description>
<pubDate>2020/1/19 17:05:07</pubDate>
<category><![CDATA[航天工程·控制科学与工程]]></category>
<author><![CDATA[GONG Zifeng, LIU Gang, SONG Rui, WU Yubin, CAI Guangbin]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>GONG Zifeng, LIU Gang, SONG Rui, WU Yubin, CAI Guangbin</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202001010]]></guid><cfi:id>8</cfi:id><cfi:read>true</cfi:read></item>
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<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Backstepping control method for hypersonic vehicles to guarantee prescribed performance]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202001011]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In order to solve the problem of stable trajectory control of hypersonic vehicle longitudinal motion model, a backstepping control method was designed to ensure the prescribed performance on the basis of non-affine model. For the velocity subsystem, the non-affine control law was directly designed to ensure the prescribed performance, and the altitude subsystem was transformed into a strict feedback form through reasonable transformation to facilitate the design of backstepping control steps. Based on dynamic performance and steady-state accuracy, the preset performance function was designed to limit the stability of tracking error within the preset range, and the instruction filter was introduced to effectively overcome the problem of repeated derivation of virtual signal in traditional inversion control. The design of the controller does not depend on the exact model. The radial basis function was introduced to approximate the unknown function in the process. As a result, the control law has satisfactory robustness and practicability. Based on the Lyapunov stability theory, the stability of all closed-loop systems was proved. Simulation results show that the controller can track the reference signal stably.]]></description>
<pubDate>2020/1/19 17:05:07</pubDate>
<category><![CDATA[航天工程·控制科学与工程]]></category>
<author><![CDATA[LI Xiaobing, ZHAO Siyuan, BU Xiangwei, HE Yangguang]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LI Xiaobing, ZHAO Siyuan, BU Xiangwei, HE Yangguang</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202001011]]></guid><cfi:id>7</cfi:id><cfi:read>true</cfi:read></item>
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<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Evolutionary-collocation hybrid optimization strategy for the multiobjective trajectory design of glider flight vehicle]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202001012]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[A hybrid optimization method combining the evolutionary algorithm and the collocation method was presented for solving the MTOP (multiobjective trajectory optimization problem) of the hypersonic glider vehicle, in which the efficiency and accuracy were balanced. According to the flight dynamic equation of the glider vehicle and the constraint condition arising in the design of the glider vehicle trajectory, the multiobjective trajectory optimization model was developed. The MTOP was transformed into the multiobjective parameter optimization problem with constraints by using the control variables discretization method; the constraint condition was dealt with the penalty function method, and the MOEA/D (multiobjective evolutionary algorithm based on decomposition) was employed to solve the problem. In order to improve the accuracy of the result, the ellipsoid aggregation method was integrated into the collocation method, in which the Pareto solution produced by the MOEA/D was the initial solution. Simulation results for MTOP with the complicated constraints demonstrate that the proposed hybrid method can generate a set of Pareto solutions, in which the gliding trajectories satisfy all the complicated constraints.]]></description>
<pubDate>2020/1/19 17:05:07</pubDate>
<category><![CDATA[航天工程·控制科学与工程]]></category>
<author><![CDATA[FENG Zhiwei, JIANG Zengrong, ZHANG Qingbin, GE Jianquan, HUANG Hao]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>FENG Zhiwei, JIANG Zengrong, ZHANG Qingbin, GE Jianquan, HUANG Hao</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202001012]]></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[Trajectory tracking using nonsingular fast terminal sliding mode control and dynamic surface control]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202001013]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Aiming at the problem of trajectory following for aerial vehicles, a nonsingular fast terminal sliding mode based trajectory following guidance law was developed. A trajectory following dynamic model with line-of-sight angle constraint considering the autopilot dynamics was established based on a virtual target moving along the desired trajectory. A desired line-of-sight angle was derived for the trajectory following problem. To follow the desired trajectory in finite time without singularity, the nonsingular fast terminal sliding mode control and the dynamic surface technique were used to design the guidance law. The mathematical relationship between the error of line-of-sight angle and the trajectory-following error was presented. The Lyapunov stability theorem was proved that the trajectory-following error was uniformly ultimately bounded. The proposed guidance law was compared with the trajectory shaping path following guidance law. The simulation results showed that the proposed guidance law provides better trajectory-following performance and has a better robustness.]]></description>
<pubDate>2020/1/19 17:05:07</pubDate>
<category><![CDATA[航天工程·控制科学与工程]]></category>
<author><![CDATA[CHEN Qi, WANG Xugang]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>CHEN Qi, WANG Xugang</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202001013]]></guid><cfi:id>5</cfi:id><cfi:read>true</cfi:read></item>
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<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Influence of plateau environment on dynamic stability of projectiles]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202001014]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The influence of low air density in the plateau environment on dynamic stability of projectiles was investigated. The force equations were presented in ballistic trajectory frame and the moment equations were presented in the non-rolling body frame, and the state space model of projectile angular motion was obtained by linearization method. Four eigenvalues of the angular motion state matrix were listed, and the equations of real parts of eigenvalues were derived by complex square root calculation method. The novel definition of stability factor for projectile dynamic stability was proposed, and it is proved that the new dynamic stability criteria is consistent with the traditional dynamic stability criteria. The influence of low air density on dynamic stability of fin-stabilized projectile and spin-stabilized projectile were discussed. Simulation results demonstrate that the projectile dynamic stability is different between plateau condition and plain condition.]]></description>
<pubDate>2020/1/19 17:05:07</pubDate>
<category><![CDATA[航天工程·控制科学与工程]]></category>
<author><![CDATA[MA Guoliang, ZHANG Haiyang, CAI Hongming, CHANG Sijiang]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>MA Guoliang, ZHANG Haiyang, CAI Hongming, CHANG Sijiang</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202001014]]></guid><cfi:id>4</cfi:id><cfi:read>true</cfi:read></item>
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<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Numerical investigation on influence of surface two-step catalytic mechanism on non-equilibrium aerodynamic heating for high-enthalpy CO<sub>2</sub> flow]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202001015]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Surface catalytic mechanism is dominated by CO<sub>2</sub> recombination during the hypersonic Mars entries, which will highly influence the aerodynamic heating. The surface CO<sub>2</sub> two-step catalytic model was dealt with on the basis of the three-dimensional compressible flow solver for chemical reaction system. The rates of surface chemical reactions were controlled by surface adsorption and Eley-Rideal recombination. The hypersonic flow around the 70° sphere-cone testing model was numerically solved to predict the chemical non-equilibrium aerodynamic heating with surface catalytic effects. The influence of two-step CO<sub>2</sub> catalytic mechanism, including two pathways, CO+O(s) and O+CO(s), on the aerodynamic heating was numerically investigated. The recombination of O<sub>2</sub> and CO<sub>2</sub> coexists and competes with each other. The catalytic heating increases monotonically with the rise of catalytic efficiency. The numerical calculation established a quantitative correlation between the catalytic pathways and the non-equilibrium heating level, and the results show that the relationships between the weight of two CO<sub>2</sub> catalytic pathways and the heating capacity are non-monotonic, and the combined aerodynamic heating of two pathways of CO<sub>2</sub> recombination is calculated to be higher than the value from single pathway. The current study contributes in several ways to our understanding of carbon-oxygen catalytic mechanism and precise evaluation of aerodynamic heating for Mars entries.]]></description>
<pubDate>2020/1/19 17:05:07</pubDate>
<category><![CDATA[航天工程·控制科学与工程]]></category>
<author><![CDATA[YANG Xiaofeng, GUI Yewei, QIU Bo, DU Yanxia, XIAO Guangming]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>YANG Xiaofeng, GUI Yewei, QIU Bo, DU Yanxia, XIAO Guangming</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202001015]]></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[Trajectory estimation for aircraft with incomplete measurements]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202001016]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[A new estimation method based on sparse optimization was proposed. This method alleviated the ill-posedness by decreasing the dimension of parameter space. The sparse representation of the trajectory was achieved by using the B-spline function. An optimization model for trajectory estimation was constructed according to the relationship between the measurement data and the trajectory, and was solved by using the Gauss-Newton method. In this model, the number of the parameters to be estimated was determined by the number of the spline knots. A sparse optimization model for optimal knot selection was established by using the discontinuity of high order derivative of spline at the knots. This model was solved by using a convex optimization approach, and the number of knots was minimized. Simulation results showed that the sparse optimization method can dramatically improve the estimation accuracy of trajectory during the incomplete measured interval.]]></description>
<pubDate>2020/1/19 17:05:08</pubDate>
<category><![CDATA[航天工程·控制科学与工程]]></category>
<author><![CDATA[LI Dong, LIU Xue]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>LI Dong, LIU Xue</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202001016]]></guid><cfi:id>2</cfi:id><cfi:read>true</cfi:read></item>
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<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Nonlinear compressed measurement identification based on Volterra series]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202001017]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[For the identification problem of nonlinear systems, the accuracy and stability of the nonlinear compression measurement identification algorithm were proved in the simulation experiment, and the complete signal was obtained accurately only by using constant multiple measurement times of the signal sparsity. Compared with the least square method, the proposed algorithm has greatly reduced the needed measurements, therefore, it is possible for the identification of high-order Volterra series. Furthermore, the influence of all factors on the accuracy of system identification was analyzed, such as signal sparsity, measurement noise, measurement matrix form, etc.]]></description>
<pubDate>2020/1/19 0:00:00</pubDate>
<category><![CDATA[航天工程·控制科学与工程]]></category>
<author><![CDATA[QIU Peng, YAO Xuri, LI Mingqian, ZHAI Guangjie]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>QIU Peng, YAO Xuri, LI Mingqian, ZHAI Guangjie</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202001017]]></guid><cfi:id>1</cfi:id><cfi:read>true</cfi:read></item>
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