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    Point precise positioning for LEO satellite based on realtime SSR data
    KANG Guohua,LIU Yao,QIAO Siyuan,JIN Chendi,GUO Yujie,LIANG Ertao
    null    DOI: 10.16708/j.cnki.1000-758X.2019.0007
    Exprimental study on thermal conductivity enhancement technique for space carbonfiber shell structure
    PANG Le, SUN Jingwen, ZHAO Kaixuan, DAI Shanliang, LIU Gang, PENG Cong
    null    DOI: 10.16708/j.cnki.1000-758X.2019.0004
    Reorganization design of taskoriented space information networks architecture
    YU Shaobo, WU Lingda, CHEN Xiaoyan, LI Chao, YAO Zhonghua
    null    DOI: 10.16708/j.cnki.1000-758X.2019.0012
    Behavior models of passive intermodulation interference in passive devices
    WU Jiayi,HU Tiancun,LIANG Bizheng,ZHANG Xuqi,LIU Celun
    null    DOI: 10.16708/j.cnki.1000-758X.2019.0009
     Onorbit intelligent identification of combined spacecraft′s inertia parameter based on deep learning
    JIN Chendi, KANG Guohua, GUO Yujie, QIAO Siyuan
    null    DOI: 10.16708/j.cnki.1000-758X.2019.0003
    A hyperspectral remote sensing image classification method based on multispatial information
    LIU Yongmei,MA Xiao,MEN Chaoguang
    null    DOI: 10.16708/j.cnki.1000-758X.2019.0013
    Study on interferometric imaging based on photonic integrated circuits
    YU Gongmin,XIAO Aiqun,JIN Libing,TONG Xiliang,ZHOU Feng
    null    DOI: 10.16708/j.cnki.1000-758X.2019.0010
    Recent progress and prospect of hightemperature heat
    pipes technology
    LI Jin-Wang, DAI Shu-Gang
    null    2019, 39 (3): 30-.   DOI: 10.16708/j.cnki.1000-758X.2019.0018
    Abstract274)      PDF(pc) (1715KB)(336)      
    Hightemperature heat pipes have a good heat transfer performance and can be used for high working temperature. They have an expansive application prospect in the field of thermal protection system of hypersonic vehicle, cooling of space reactor and utilization of solar energy, and so on. The recent progress of hightemperature heat pipes is reported,including the startup characteristic from the frozen state and heat transfer performance of hightemperature heat pipes, the experimental studies, the numerical analysis studies. The effects of the inclination angles, the working fluid parameters, the fill charge ratio, the noncondensable gas, the material, the structure and the sizes on the startup characteristic from the frozen state and heat transfer performance of hightemperature heat pipes are presented.The applications of hightemperature heat pipes for thermal management of hypersonic flight vehicles, cooling of space reactor and utilization of solar energy are summarized. The future development direction is also pointed out, such as the numerical analysis model and engineering application of hightemperature heat pipes. The future research suggestions of hightemperature heat pipes are also put forward.
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    Scheme design and analysis of recoverable sounding rocket reducer
    YANG Jian-Yu, YANG Xuan
    null    2019, 39 (5): 1-.   DOI: 10.16708/j.cnki.1000-758X.2019.0034
    Abstract262)      PDF(pc) (2810KB)(109)      
    In order to meet the requirements of the rapid recovery of sounding rocket and reduce the development cost,a new type of sounding rocket skirt reel deceleration program was proposed. It has light weight,changeable expansion angle,expanded resistance area and some other advantages. The aerodynamic characteristics of the supersonic sounding rocket reducer were analyzed, the external flow field was simulated and analyzed. The influence of different taper angles on the aerodynamic characteristics and overload was given. The stress and strain of the external flow field, the pressure field and the gear unit were presented. The results show that the pneumatic resistance of the gear unit is obviously related to its cone angle and has the nonlinear characteristics, and the maximum stress of the reducer is less than the allowable stress. This paper can provide reference for the design of sounding rocket and new reducer.
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    Orbit control force coefficient identification by Charp recursion method
    ZHANG Ying,WANG Xijing,YUAN Bo,KONG Dalin,BIAN Yanshan
    null    DOI: 10.16708/j.cnki.1000-758X.2019.0011
    Spacecraft attitude measurement based on samebeam interferometry
    ZHANG Tiangang,REN Tianpeng,XIE Jianfeng,LU Weitao,YIN Feifei
    null    DOI: 10.16708/j.cnki.1000-758X.2019.0008
    Online design of optimal carrier tracking loop bandwidth for tightlycoupled GPS/INS
    XU Xiaohan, WANG Kedong
    null    DOI: 10.16708/j.cnki.1000-758X.2019.0005
    Lunar surface sampling point selection for uneven terrain
    ZHENG Yanhong, YAO Meng, JIN Shengyi, ZHAO Zhihui, DENG Xiangjin ,HE Xiaoyang
    null    DOI: 10.16708/j.cnki.1000-758X.2019.0006
    Research and realization of model based satellite telemetry and command information flow digital design method
    YE Mian, HAN Xiao-Dong, HAO Yan-Yan, WANG Yi-Yi
    null    2019, 39 (3): 71-.   DOI: 10.16708/j.cnki.1000-758X.2019.0021
    Abstract213)      PDF(pc) (3118KB)(146)      
    Information flow design for telemetry and command(T&C) is one of the essential parts of satellite general information design. The information flow design for telemetry and command reflects the movement of telemetries and commands. Satellite resource distribution and onboard equipment layout are determined by the rationality and validity of design result. Nowadays, traditional T&C information flow design method cannot satisfy the requirements of digital design mode and increasing assignment demand. To solve these problems, a new modelbased satellite T&C information flow digital design method is proposed by using graphic equivalent model. This method not only remedies the disadvantage of traditional design method, but also can be used in optimal design. This method has been tested by a satellite project,and test result shows that manhour is reduced by 975%. At the same time, the validity reaches 100%. It is proved that the new method can increase design efficiency, enhance designing quality, and improve standardization of T&C information flow design process, method and product. Moreover, it can promote the automatization level of information flow design.
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    Satellite video pointtarget tracking  based on Hu correlation filter
    WU Jia-Qi, WANG Tao-Yang, YAN Jun, ZHANG Guo, JIANG Xiao-Hua, WANG Yun-Ming, BAI Qian, YUAN Chong
    null    2019, 39 (3): 55-.   DOI: 10.16708/j.cnki.1000-758X.2018.0059
    Abstract202)      PDF(pc) (4317KB)(300)      
    Aiming at the moving object tracking problem of satellite video, a robust method of feature description and matching based pointtarget tracking is proposed. The idea of correlation filter is introduced. Firstly, Hu invariant moments and median filtering of the sample set are used to establish the tracking template of the target and describe the target features. Then, the dimension of the decision area of target tracking is reduced and the Hu confidence model of the judgment area is established. Finally, the target tracking is achieved by finding the maximum value of the tracking confidence map by using the fast FFT derivation correlation method. Moreover, the robustness of the algorithm is improved by using Kalman filtering to assist and optimize the tracking process. The experimental video data are taken from SkySat1 and Jinlin1 satellites. The tracking experiments of 5 point targets show that the proposed method achieves good results in the satellite video, and that the accuracy is better than 90%. The target is not lost in the whole tracking process and the tracking trajectory is smooth. In addition, for the 13×13 judgment area, the processing speed of the confidence map is about 5 times higher than the conventional correlation method. This method can provide a technical basis for achieving fast and reliable tracking of point targets in satellite video.
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    Recent advances of multipactor suppression by surface treatment for highpower microwave components in China
    SONG Qiang-Qiang, CUI Wan-Zhao, YANG Jing, HU Tian-Cun
    null    2019, 39 (3): 43-.   DOI: 10.16708/j.cnki.1000-758X.2019.0019
    Abstract195)      PDF(pc) (4096KB)(170)      
    The Secondary Electron Emission (SEE) from materials used in highpower RF devices in space is the main trigger and sustaining mechanism of the resonant avalanche electron discharge known as the multipactor effect. Multipactor effect is one of the key issues to limit the application of highpower microwave components in space. Starting from the mechanism of multipactor, the basic physical mechanism of two types of multipactors (singlesurface and twosurface)is briefly introduced, and then the current mainstream of multipactor suppression methods are summarized and the limitations of their respective applications in space highpower microwave components are given. Finally, focusing on the special problem of multipactor suppression in aerospace highpower microwave components, the research work on surface treatment to inhibit multipactor in the past five years is reviewed and the tendencies of multipactor suppression technology are predicted.
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    Research progress of electromagnetic sail propulsion for deep space exploration
    YU Wei-Dong, WEN Xiao-Dong, ZHANG Tian-Ping, LIU Li-Juan
    null    2019, 39 (4): 43-.   DOI: 10.16708/j.cnki.1000-758X.2019.0028
    Abstract185)      PDF(pc) (5928KB)(178)      
    Electromagnetic sail, a kind of space propulsion technology driven by solar wind, has broad application prospects in deep space exploration missions that require spacecraft working for a long time due to its characteristics of no propellants or less propellants. The basic concepts and main classifications of the electromagnetic sails are introduced. The working principles, system compositions, research status of ESail,PMS and MPS are discussed and followed by the plasma magnetoshell technology. Finally, the research progress of electromagnetic sail propulsion technology is summarized, which provides research direction and development ideas for domestic research in this field.
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    Analysis of influence of solar radiation pressure on ground track keeping control in zero yaw attitude mode
    ZENG Guang, WU Xin-Lin, GONG Bing, LI Dong-Lin, WANG Chao
    null    2019, 39 (3): 23-.   DOI: 10.16708/j.cnki.1000-758X.2019.0017
    Abstract180)      PDF(pc) (4126KB)(153)      
    The intrinsic "anomaly"  mechanism of the ground track drift of a satellite in orbit is analyzed and the model of solar radiation pressure accumulation effect in alongtrack direction in zero yaw attitude mode(keeping yaw angle zero in one orbit cycle) is built. Then, the model parameters are estimated using historical observation data through POD. Finally, the accuracy of the new model is verified by using the real ground track of the satellite in 2018. The results show that the accuracy of satellite ground track drift forecast is significantly improved by using the new model. It can provide technical support for developing the control strategy of ground track keeping for this kind of satellite.
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    Analysis and simulation of influence factors of spacebased optical space debris detection
    XING Bi-Da, XIN Tian, ZHENG Chang-Wen
    null    2019, 39 (3): 9-.   DOI: 10.16708/j.cnki.1000-758X.2019.0015
    Abstract180)      PDF(pc) (6312KB)(153)      
    Optical methods are widely used in spacebased space debris detection, but they are vulnerable to stray light and other factors The factors which affect spacebased optical space debris detection are analyzed from the two aspects of detectors and debris based on the experimental data The factors affecting the detection effect include stray light such as sunlight, moonlight, earthatmosphere light and airglow, as well as radiation in South Atlantic Anomaly region The factors affecting the visibility of debris include earth occlusion, earth shadow and reflected sunlight At the same time, the characteristic quantities involved in the above factors and the calculation methods to avoid the effects are put forward The simulation results of a spacebased detection equipment show that the above effects may occur in both normal rendezvous and attitude maneuver modes, so that they should be fully considered in the experiment design Finally, a spacebased space debris detection mission is planned The article has certain guiding significance for the experiment design of spacebased optical detection.
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    Thrust and specific impulse tests of miniature gallium field emission electric propulsion thruster
    XU Ming-Ming, LIU Xin-Yu, KANG Xiao-Ming, GUO Deng-Shuai, HE Wei-Guo
    null    2019, 39 (5): 69-.   DOI: 10.16708/j.cnki.1000-758X.2019.0042
    Abstract178)      PDF(pc) (3215KB)(114)      
    The development of electric propulsion technology has promoted the research process of micro thrust measurement technology and specific impulse measurement technology. In order to evaluate the performance of the developed miniature gallium field emission electric thruster, thrust and specific impulse measurements were made. A thrust measurement platform for field emission electric thrusters was developed, the LabVIEW development was carried out and the measurement platform was calibrated and analyzed. The measured values and theoretical values of the thrust were compared through experiments. The measured values range from 3 to 28μN. In addition, using the time of flight method, the thruster′s specific impulse data under different emission currents were measured, and the specific impulse′s range is 5917-8875s.
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