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Table of Content

    25 February 2002, Volume 22 Issue 01 Previous Issue    Next Issue
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    Adaptive Internal Model Control of Satellites With Flexible Appendages
    Zhang Honghua Zhang Guofeng ( Beijing Institute of Control Engineering,Beijing10 0 0 80 )
    2002, 22 (01):  . 
    Abstract ( 1575 )   Save
    To guarantee the attitude control performance of the large satellite,the mathematical model with flapping motion is derived,the simple controller form is given and the adaptive internal model control is proposed.The analytical and simulation results show that the adaptive internal model control is very effective for the precision control of the large satellites.
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    Study on Hardware Compression System Architecture for RBC Algorithm
    Cheng Zijing Zhou Xiaokuan ( Beijing U niversity of Aeronautics and Astronautics,Beijing 10 0 0 83 )
    2002, 22 (01):  . 
    Abstract ( 1467 )   Save
    VL SI architecture based on the RBC algorithm is developed. The architecture is fastwith low hardware complexity,which can compute huge amount of data at very high speed for real- time compression application and match the requirement of VL SI architecture,regularity,modularity,locality.Based on the architecture,special chip for real- time image compression is designed and manufactured with Field Programmable Gate Array.The peak processing speed of the ASIC can reach2 88Mbit/s and their power consumption is lower than1W.
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    Adaptive Attitude Control for Small Satellite
    Wang Jing L iu L iangdong Zhang Duzhou ( Beijing Institute of Control Engineering,Beijing10 0 0 80 )
    2002, 22 (01):  . 
    Abstract ( 1555 )   Save
    The attitude dynamics and kinematics of small satellite are analysed.The dynamic equation can be linearized by a vectorof dynamic parameters.By this property and in the presence of parameter uncertainty,an adaptive control algorithm is presented,and the algorithm can keep the control system increasingly stable.Simulation results confirm the effectiveness of the algorithm.
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    The Recursive Calculation of Spline Function L east Square Approximating
    Zhu Zhuanmin Yang Yikang Huang Yongxuan ( Institute of System Engineering,Xi' an Jiaotong University,Xi' an710 0 4 9) L i Jisheng ( Xi' an Satellite Control Centre,Xi' an 710 0 4 3 )
    2002, 22 (01):  . 
    Abstract ( 1856 )   Save
    In currently range data processing,the estimate of parameters and patch calculating usually use polynomial to approximate,which often make much more truncation errors.A method to approximate the trajectory by using the fine nature of spline functions as the base is proposed.Through integrating the spline function and recursive,a recursive calculation of spline function leastsquare approximating approach is given.The simulation demonstrates the method can save memory of computer and improve the accuracy and speed greatly.It is a practice method in project.
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    Mistakes of Rotational Direction of Circularly Polarized Antenna
    Zhang Zhaoyan ( Beijing Institute of Space Science and Technology Information,Beijing 10 0 0 86)
    2002, 22 (01):  . 
    Abstract ( 1595 )   Save
    The reasons which often cause mistakes of rotational direction of circularly polarized wave are described.Basic conception and definition of circularly polarized wave and antenna are presented.To avoid mistakes of rotational direction of circularly polarized wave,two items of the useful recommendation are provided.
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    Strategic Reserve for Space Remote Sensor
    Yang Hua Fu Ruimin ( Beijing Institute of Space Machine and Electricity,Beijing10 0 0 80 )
    2002, 22 (01):  . 
    Abstract ( 1742 )   Save
    Remote sensing technology has developed rapidly during the last decades. Thus,space remote sensor,whatevernew type orolder type to be,should be keptreserve for normal or emergency use.According to this opinion and the research and development of remote sensing in China,the necessity and feasibility of strategic reserve for the space remote sensor is analysed and discussed.
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    Research of Algorithm for Seeking Feasible Project of Remote Guidance
    Han Chao Duan Bin Fu Hongxun ( Beijing U niversity of Aeronautics and Astronautics,Beijing10 0 0 83 )
    2002, 22 (01):  . 
    Abstract ( 1490 )   Save
    Remote guidance of space rendezvous usually meet the requirements of measure,sun- lighting,fuel and time.An algorithm of seeking feasible project of remote guidance is issued,which focuses on L ambert orbit transfer.Finally a given case of calculation proves this algorithm is feasible.
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    Sensitivity Calculation Formulas of Leakage Detecting Method
    Yan Zhiping Huang Shuying ( Beijing Spacecraft,Beijing 10 0 0 80 )
    2002, 22 (01):  . 
    Abstract ( 1390 )   Save
    The sensitivity calculation formulas of general leakage detecting methods are developed for the some objectives of selected leakage detecting method,designed leakage detecting system and calibrated system sensitivity.The formulas for the leak detection are applied in a sealed system .
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    The Design of FY-2 Satellite Transponder
    L i Bingshang ( Xi' an Institute of Space Radio Technology,Xi' an710 0 61)
    2002, 22 (01):  . 
    Abstract ( 1838 )   Save
    The design of FY- 2 satellite transponder is summarized,including its function,technical performance as well as some problems being solved during the development.These problems were the high sensitivity of command receiver,the reducing of modulation noise of remote control and the wide tracking modulation bandwidth. It could be a beneficial reference for the associated engineers or technicians.
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    The New Technology Experiment of the Payload Data Management System
    Chen Xiaomin Sun Huixian ( Center for Space Science and Applied Research, Chinese Academy of Sciences,Beijing 10 0 0 80 )
    2002, 22 (01):  . 
    Abstract ( 1513 )   Save
    The first Payload Data Management System( PDMS) has been developed in China to meetthe requirements of the data acquisition,processing,recording,transmission as well as data handling for the payloads of the science experiments and space exploration on the spacecraftin future. The designs of the system adoptseveral advanced technologies corresponding to international levels of the 1990 ' s such as data transmission according to the CCSDS standard,data communication network based on15 5 3 B data bus,mass solid state recorder technology,High Rate Multiplexer and management software of PDMS. PDMS and its technical characteristics,the design and implementation of the key techniques of the system are described. The onboard test results of the miniature system composed of the key techniques in the mission of satellite are also given.
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    Wide-band Random Vibration Response Prediction Study of the Spacecraft Structures
    Han Zengyao Qu Guangji ( Beijing Institute of Spacecraft System Engineering,Beijing10 0 0 86)
    2002, 22 (01):  . 
    Abstract ( 1578 )   Save
    The significance of the research related to the wide- band random vibration analysis on spacecraft and the developing history and recent status home and abroad arsummarized briefly.Then,the hybrid application of Finite Element Method and Statistical Energy Analysis is used to predict the response of the whole satellite under wide- band random vibration excitation and the prediction resultaccordswith thatof experimentwell.
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