<?xml version="1.0" encoding="utf-8"?>
<rss version="2.0" xmlns:atom="http://www.w3.org/2005/Atom" xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005">
<channel xmlns:cfi="http://www.microsoft.com/schemas/rss/core/2005/internal" cfi:lastdownloaderror="None">
<title cf:type="text"><![CDATA[Editorial department of the Journal of National University of Defense Technology -->航天工程·光学工程]]></title>
<item>
<title xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="text"><![CDATA[Generalized finite integral transform method for dynamic characteristic analysis of nonlocal thin plate]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202201010]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The generalized finite integral transform method was applied to get the dynamic characteristic of a nonlocal thin plate based on the stress gradient nonlocal theory. The integral transform pairs were established by using the integral kernels which can satisfy the boundary conditions. The higher-order partial differential equation of the nonlocal thin plate was transformed in to a series of linear algebraic equations through the integral transform, and the nature frequencies of the governing equations can be solved exactly. To confirm the validity of the simulated, the results were compared with the finite element method and the existing ones. The effects of the nonlocal parameter and the dimension of the plate on the nature frequency were studied. The proposed method provides a new way to solve the mathematical problem of the nonlocal plate problem.]]></description>
<pubDate>2022/1/19 9:20:44</pubDate>
<category><![CDATA[航天工程·光学工程]]></category>
<author><![CDATA[JIANG Renwei, YANG Shutao, ZHAO Jiamin, LI Daokui, MA Weili]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>JIANG Renwei, YANG Shutao, ZHAO Jiamin, LI Daokui, MA Weili</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202201010]]></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[Flexible spacecraft attitude maneuver planning based on variable amplitudes input shaping method]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202201011]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In order to solve the attitude maneuver problem for flexible spacecraft with time-varying parameters, the variable amplitudes zero vibration derivative shaper with stronger robustness was developed based on the variable amplitudes zero vibration shaper. The robust attitude maneuver strategy, in which its objective was to maneuver the spacecraft to the desired attitude state and cancel the residual vibration of the rotating flexible appendages at the same time, was proposed. Simulations were conducted by means of a spacecraft with rotating solar wings which undergoes three-axis maneuvers. The results indicate that this strategy is robust to frequency variations, uncertainties of damping coefficient and other uncertain factors.]]></description>
<pubDate>2022/1/19 9:20:44</pubDate>
<category><![CDATA[航天工程·光学工程]]></category>
<author><![CDATA[WANG Jie, WU Jun, ZOU Jie]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>WANG Jie, WU Jun, ZOU Jie</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202201011]]></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[Compatibility multi-dimensional analysis method for geostationary satellite orbit systems]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202201012]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Aiming at the compatibility analysis between GSO (geostationary satellite orbit) satellite systems, uplink and downlink interference scenarios were designed between single-beam and multi-beam GSO satellite systems, and GSO satellite systems interference was evaluated on multiple dimensions, such as satellite orbital position, system link availability, and interference system′s earth stations location. Recommendations were proposed on the nearest location of interference system′s earth stations at different orbital intervals, which met International Telecommunication Union limit. The granularity of each dimension was refined. Different dimensions were compared horizontally, and interference variation characteristic curves and the influence level of each dimension were analyzed. When link availability was fixed, the interference value changed slowly with the orbital interval at >2°, the interference value changed rapidly with the interval at ≤2°, especially when the interval was at≤0.1°, the interference value rose sharply. Taking network data of the CHNSAT-81.5 and INSAT-KA82.5E satellites registered by the International Telecommunication Union as examples, the interference-to-noise ratio and the carrier-to-interference ratio were compared with Visualyse, the result error was kept in the range of 0.7 dB with an effective evaluation performance.]]></description>
<pubDate>2022/1/19 9:20:44</pubDate>
<category><![CDATA[航天工程·光学工程]]></category>
<author><![CDATA[DONG Suhui, GAO Xiang, HAN Rui, YAO Xiujuan, YAN Yi]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>DONG Suhui, GAO Xiang, HAN Rui, YAO Xiujuan, YAN Yi</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202201012]]></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[Experimental study on the passive boundary layer control methods of chemical oxygen-iodine laser cavity]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202201013]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[Aiming at the passive boundary layer control methods of COIL (chemical oxygen-iodine lase) cavity, three types of experiment rigs were designed. The upper and bottom walls of laser cavity are removable, so the boundary layer control effect with different experiment rigs can be compared. The experiment results indicate that the thickness of boundary layer in laser cavity can be reduced by both slotted wall, mainstream ejected slot and perforated wall. The pressure distribution in cavity, especially in the latter of cavity, is improved. The boundary layer thickness can be reduced further by increasing the sucking rate in a proper range, meanwhile the cavity pressure can be dropped and the COIL power can be increased. But the COIL power also can be dropped with the overlarge sucking rate. Among the three experiment rigs, the mainstream ejected slot is the most sensitive to sucking rate, that when the sucking rate improved to 5%, the COIL power drops obviously. The perforated wall is the most insensitive to sucking rate, and the COIL power has little change while the sucking rate improved from 1% to 7%.]]></description>
<pubDate>2022/1/19 9:20:44</pubDate>
<category><![CDATA[航天工程·光学工程]]></category>
<author><![CDATA[XU Dachuan, GU Yunsong, REN Zebin, CHEN Zhiqiang, WANG Haifeng]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>XU Dachuan, GU Yunsong, REN Zebin, CHEN Zhiqiang, WANG Haifeng</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202201013]]></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[Numerical analysis for aerodynamic characteristics of electromagnetic launch hypervelocity projectile]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202201014]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[The numerical method was used to study the aerodynamic flow field characteristics of hypervelocity projectiles, especially in the reentry phase. The prediction accuracy of S-A and k－ω SST turbulence model was verified by wind tunnel test data. The calculation results show that the prediction accuracy of the two turbulence models is higher than 2% in normal force prediction. In axial force prediction, the S-A turbulence model has a high prediction accuracy of 4.6%. When the projectile reenters at a large angle of attack, the transverse flow effect of projectile is more obvious. The shock wave makes the surface pressure of the projectile increase sharply on the windward side, while the large-scale streamwise vortex structure formed on the leeward side reduces the pressure, and the increase of the pressure on the windward side has a greater impact on the aerodynamic coefficient of projectile. The aerodynamic drag and lift coefficient at high angle of attack are obviously nonlinear, the drag coefficient is obviously increased, and the static stability margin is also sharply reduced, which makes the convergence characteristics of projectile worse, and that is treated as the main reason for the velocity attenuation during the reentry process of projectile.]]></description>
<pubDate>2022/1/19 9:20:44</pubDate>
<category><![CDATA[航天工程·光学工程]]></category>
<author><![CDATA[FENG Junhong, LU Junyong, LI Kai, LI Xiangping]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>FENG Junhong, LU Junyong, LI Kai, LI Xiangping</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202201014]]></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[Investigation on thermal protection of opposing jet for nosecone in hypersonic flow using a fluid-thermal coupled method]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202201015]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[As one of the active cooling methods, the opposing jet shows its advantages on the aerodynamic thermal reduction for hypersonic flight. To accurately predict the thermal protection properties of the opposing jet, the numerical investigation on the flow and heat transfer characteristics for the opposing jet of nosecone at Mach 6 was conducted by using a fluid-thermal coupling strategy. The related turbulent model and fluid-thermal coupled method were validated by the comparison of the numerical and experimental results. Flow patterns of the opposing jet with different total pressure ratio were gained, and the influence of the total pressure ratio of the opposing jet on the heat transfer between fluid and solid structure was discussed. Besides, the influences of attack angle and solid materials on structural heat reduction were also investigated. The numerical results indicate that:the increase of total pressure ratio of the opposing jet brings obviously further heating reduction, and accordingly the solid structure temperature presents more uniformity; calculation of the heating in 60 s indicates that the positive attack angle enlarges the temperature difference in the solid structure, which induces the lower temperature air flowing to the leeward side furtherly, so the cooling for the leeward side of nosecone is enhanced; for alloy IN718 and C-103 two different materials, their discrepancy of heating can be neglected at the cooling recirculation region of nosecone and the area where the recompression shock influence obviously; in comparison, the use of C-103 shows its advantage of even distribution of temperature in the internal system of structure.]]></description>
<pubDate>2022/1/19 9:20:44</pubDate>
<category><![CDATA[航天工程·光学工程]]></category>
<author><![CDATA[YIN Liang, LIU Hongpeng, LIU Weiqiang]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>YIN Liang, LIU Hongpeng, LIU Weiqiang</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202201015]]></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[Numerical analysis on structural integrity of finocyl grain under ignition loading]]></title>
<link><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202201016]]></link>
<description xmlns:cf="http://www.microsoft.com/schemas/rss/core/2005" cf:type="html"><![CDATA[In order to study the structural integrity analysis of finocyl grain for solid rocket motor under the ignition loading, a numerical simulation method with considering the three-dimensional damage viscoelastic constitutive was proposed. The commercial finite element software was taken to the secondary development, and the user subroutine was written. Therefore, the numerical simulation was carried out. The distribution of stress, strain and displacement filed of finocyl grain were obtained under the condition of the temperature loading and ignition pressure. Results show that the deformation mode of inner surface of grain is different under the temperature loading and ignition loading. However, regardless of the temperature loading or ignition loading, both the Von Mises stress and Von Mises strain in the fin-slot region of grain are higher than those in other parts. This method can be applied to the security assessment of structural integrity analysis of solid rocket motor.]]></description>
<pubDate>2022/1/19 9:20:44</pubDate>
<category><![CDATA[航天工程·光学工程]]></category>
<author><![CDATA[GONG Jianliang, JIN Bingning, GONG Wanjun, DENG Zhe, ZHANG Zhengze]]></author>
<atom:author xmlns:atom="http://www.w3.org/2005/Atom">
<atom:name>GONG Jianliang, JIN Bingning, GONG Wanjun, DENG Zhe, ZHANG Zhengze</atom:name>
</atom:author>
<guid><![CDATA[http://journal.nudt.edu.cn/gfkjdxxben/article/abstract/202201016]]></guid><cfi:id>1</cfi:id><cfi:read>true</cfi:read></item>
</channel>
</rss>