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    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
    Abstract342)      PDF(pc) (1715KB)(390)      
    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
    Abstract285)      PDF(pc) (2810KB)(137)      
    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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    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
    Abstract245)      PDF(pc) (4096KB)(200)      
    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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    Feasibility analysis of airbreathing plasma propulsion system
    YANG Zhaolun, GUO Ning, CHEN Xuekang, YAN Nengwen, WANG Cong
    Chinese Space Science and Technology    2020, 40 (1): 54-.   DOI: 10.16708/j.cnki.1000-758X.2020.0007
    Abstract238)      PDF(pc) (1591KB)(223)      
    The airbreathing plasma propulsion system has been studied as a potential technology for longlife super low altitude flight. According to different orbital environmental conditions, the feasibility of the airbreathing plasma propulsion system was discussed by using the tubular inlet and the mechanical pressurization suction method. The analysis shows that the ratio of the total power required by the spacecraft to the windward surface should be greater than 2kW/m2, and that the specific impulse of the plasma thruster should be greater than 4×104m/s, so as to meet the requirements of pushdrag balance. It is pointed out that in order to realize the application of suction system in earth orbit, the key technology is to increase gas collection efficiency and reduce collection power consumption, while the efficiency of plasma thruster needs to be further improved.
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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
    Abstract237)      PDF(pc) (5928KB)(211)      
    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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    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
    Abstract234)      PDF(pc) (3118KB)(163)      
    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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    Attitude and orbit coupling control for fly-around observation of multi-satellite proximity operation
    XU Ying, ZHANG Jin, YU Moyao, XU Dandan
    Chinese Space Science and Technology    2019, 39 (6): 21-.   DOI: 10.16708/j.cnki.1000-758X.2019.0046
    Abstract222)      PDF(pc) (6611KB)(129)      
    Aiming at the observation mission of multi-satellite proximity operation, dynamics models of relative attitude and orbit are established. Two kinds of desired triangular formation configurations of observation satellites in elliptical and space circular orbits are considered respectively. The desired attitude is designed that the observation satellite's line of sight always points to the target satellite. The proportional-differential control law based on the quaternion and angular velocity error feedback and an improved guidance method based on artificial potential field method are used to control the relative attitude and orbit. The simulation results show that all observation satellites can effectively track the desired relative attitude and desired relative orbit under the action of the control law. In the triangular formation configuration of space circular orbit, after starting from the same initial position, the formation configuration of three observation satellites always keeps a regular triangle. Moreover, the side length of the regular triangle increases gradually from zero to finally the desired value.
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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
    Abstract217)      PDF(pc) (4317KB)(327)      
    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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    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
    Abstract211)      PDF(pc) (3215KB)(143)      
    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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    Preliminary design and test of attitude control system for lunar CubeSats
    YANG Chi-Hang, LIU Jiang-Kai, LONG Long- , SONG Huan, LI Long, ZHU Ling-Chao, YE Bing-Xu, CHEN Hong-Ru, ZHANG Hao
    null    2019, 39 (4): 28-.   DOI: 10.16708/j.cnki.1000-758X.2019.0026
    Abstract210)      PDF(pc) (2728KB)(162)      
    CubeSats are miniature functional satellites The increasing interest in CubeSats has uncovered the potential for planetary missions Besides, CubeSats is an excellent educational platform. The preliminary attitude control system is designed and the corresponding hardware is built using commercial products for a lunar mission employing a CubeSat constellation to provide positioning service for landers/rovers on the far side of the moon At the same time, the basic frame and necessary subsystems including the structure, power and onboard computer subsystems, and the attitude experiment platform are constructed Based on the hardware platform, the control model is deeply understood through measuring damping coefficients by experiments A PD control method is designed to control the attitude The numerical and physical simulation results match well, and the CubeSat system achieves accurate attitude maneuver.
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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
    Abstract207)      PDF(pc) (6312KB)(196)      
    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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    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
    Abstract201)      PDF(pc) (4126KB)(174)      
    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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    Space microgravity combination and its control
    YU Shao-Hua
    null    2019, 39 (5): 49-.   DOI: 10.16708/j.cnki.1000-758X.2019.0039
    Abstract193)      PDF(pc) (1448KB)(144)      
    Space microgravity combination is an upgraded version of the tethered satellite system, a more powerful and prospective version for future applications. However, both the systems are beset with the same problem: if there is no preset control,the system′s motion is unstable. Therefore, an effective control algorithm has to be developed to make the system stable. Based on a simplified dynamic model of tethered satellite,the relationship between microgravity and dynamic inertia forces was used to deduce a very unique range rate control algorithm to stabilize the system concisely and productively. This algorithm can be applied to massdistributed, elastic and other more complex cases of tethered satellite control. It can also be successfully adopted to control inorbit rendezvous and docking missions of the space microgravity combination.
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    High power electrodeless electromagnetic propulsion based on high density plasma: a review
    LIU Li-Juan, WEN Xiao-Dong, SUN Xin-Feng, ZHANG Tian-Ping, GUO Ning
    null    2019, 39 (5): 37-.   DOI: 10.16708/j.cnki.1000-758X.2019.0038
    Abstract190)      PDF(pc) (4869KB)(252)      
    High power electrodeless electromagnetic propulsion based on high density plasma has already become one of the most competitive core propulsion technologies in future space missions, such as deep space exploration, manned space flight, solar power station and onorbit maintenance and service. Based on the different acceleration mechanisms adopted in different electrodeless electromagnetic propulsion technologies, the propulsion performances of different electromagnetic propulsion technologies were compared.Then the field reversed electrodeless electromagnetic propulsion technology adopting the rotating magnetic field acceleration mechanism was analyzed,which has great advantages and potential in developing to super high power propulsion thruster. At last, the existing technical challenges confronted in developing this new conceptual thruster was presented, aiming at providing technical and theoretical supporting for the future development of the field reversed electrodeless electromagnetic propulsion technology.
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    Development and ignition characteristics of miniature gallium field emission electric propulsion thruster
    XU Ming-Ming, KANG Xiao-Ming, GUO Deng-Shuai, LIU Xin-Yu, HE Wei-Guo
    null    2019, 39 (4): 73-.   DOI: 10.16708/j.cnki.1000-758X.2019.0032
    Abstract189)      PDF(pc) (3944KB)(175)      
    In order to meet the demand for propulsion systems of micronano spacecraft such as the cubic satellite, the first needletype miniature gallium field emission electric propulsion thruster in China was developed. The problem that gallium is difficult to fully wet the tungsten needle under vacuum environment was solved by increasing the wetting temperature. The thruster′s stable ignition was realized, and the thruster′s ignition characteristics under different wetting temperatures and different geometric parameters were tested. The relationship is obtained that the emission current increases as the wetting temperature increases, the pole spacing decreases, and the inner hole diameter of absorbing pole increases. The theoretical thrust under different emission currents is given by formula calculation.The electric field strength under different geometric parameters is obtained by simulation, and the reason why the geometric parameters affect the emission current is revealed.
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    Miniaturization design and implementation of solidstate currentlimit protection circuit for space
    NI Chun-Xiao, ZHAO Guo-Qing
    null    2019, 39 (3): 17-.   DOI: 10.16708/j.cnki.1000-758X.2019.0016
    Abstract189)      PDF(pc) (1346KB)(482)      
    A solidstate currentlimit protection circuit with command control mode,onoff indication and currentlimit protection adjustment function is designed to replace the fuse in the space power bus for inrush current suppression and load overcurrent protection In order to meet the miniaturization design requirements of the products, the circuit adopts thick film process layout and wiring, and is manufactured by microassembly technology Through circuit simulation, layout design and application testing, the circuit performance meets the design requirements, and the product size is only 25mm×23mm×55mm, showing significant advantages in miniaturization design As an emerging solidstate power distribution protection product, it has broad application prospects in space power supply and distribution system。
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    An electric thrust vector calibrating algorithm using angular momentum
    CUI Zhen-Jiang, ZHOU Liang, HU Shao-Chun, GONG Jian-Jun
    null    2019, 39 (3): 1-.   DOI: 10.16708/j.cnki.1000-758X.2019.0014
    Abstract186)      PDF(pc) (3310KB)(252)      
    More and more electric propulsion (EP) systems have been used on spacecraft for orbit correction. The configuration, installation and usage modes of electric thruster determine the adjustment strategy of EP. In most cases, the satellite in orbit needs calibration and adjustment of the electric thrust vector. An algorithm to calibrate and adjust the electric thrust vector of a certain type of GEO satellite using the change of angular momentum was presented, as well as an application case of this algorithm in orbit for the first time in China. The result of inorbit calibration suggests that the algorithm is correct and practical, providing a solution for the calibration and adjustment of EP on satellite.
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    Study on the inhibition effect of modified Allan variance on Flicker PM noise
    LIU Ying-Qian, CHEN Qiang, XUE Ren-Kui, LAN Xue-Mei, ZHANG Zhen-Zhi
    null    2019, 39 (4): 68-.   DOI: 10.16708/j.cnki.1000-758X.2019.0031
    Abstract180)      PDF(pc) (1184KB)(170)      
    In the time and frequency field, Allan variance is utilized in general to indicate frequency stability. Allan variance can not inhibit Flicker PM effectively because it′s defective algorithm. In order to reduce the impact of noise on frequency stability, frequency stability should be indicated by modified Allan variance. Modified Allan variance for inhibition mechanism of Flicker PM is analyzed. Through the satellite commonview method, the comparative data of hydrogen clock and UTC(NIM) are evaluated. Then, the noise model is used to demonstrate the results of evaluation. The effectiveness of the modified Allen variance against Flicker PM inhibition is verified.
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    Investigation of the Sband electromagnetic wave attenuation by the Hall thruster plume
    YU Bo, ZHANG Min, YU Shui-Lin, KANG Xiao-Lu
    null    2019, 39 (5): 19-.   DOI: 10.16708/j.cnki.1000-758X.2019.0036
    Abstract173)      PDF(pc) (11601KB)(112)      
    The Hall thruster plume exerts an attenuation influence on Sband electromagnetic wave and plays an important role in the layout strategy of the thruster and antenna on the satellite. In order to study the law of the signal attenuation, an algorithm of geometric lightpath was established to numerically describe the transportation of electromagnetic wave in Hall plume. A rectification test of the algorithm accuracy was conducted, and the signalnoise ratios (SNR) were measured by the method of wave transmission in space. According to the test and calculation results at same operation cases, the maximum relative error was 26.1%, and the average relative error was 7.3%. The calculation results kept qualitatively consistent with the test results. Based on those, the 84 typical operation cases of the SNR attenuation of the Sband electromagnetic wave were computed. The calculation results show that the absorption by plume exerted a more remarkable effect than the reflection on signal attenuation, and that the max attenuation region covered the antenna position of 0.3-0.6m,the direction angle of 15°-30°, and the attenuation value of SNR between -7dB and -4dB. This paper provides a reference base for the layout strategy of the thruster and the antenna on satellites.
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    Application of selfadaptive fuzzy PID technology in launch site gas supply system
    YANG Yi-Qi, LIU Hao-Yang, YUE Long-Hua, WANG Tian-Hang
    null    2019, 39 (3): 81-.   DOI: 10.16708/j.cnki.1000-758X.2019.0022
    Abstract168)      PDF(pc) (2252KB)(181)      
    Aiming at the problems of nonlinear pressure control, large timelag and variable parameters, a closed loop pressure control system is designed based on selfadaption fuzzy PID technology. By online adjusting of the proportional coefficient Kp,the integral coefficient Ki and the differential coefficient Kd of the controller, high precision control of the pressure is realized. Based on the test data, a secondorder lag inertia model is established by curve fitting and simulation. The simulation verifies the validity of the model. The conclusion shows that this control effect is better than the conventional PID control, and can effectively improve the dynamic performance and steadystate accuracy of the system. It can be widely used in the automatic control system of the launch site where PLC control is a core method.
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