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Table of Content

    25 December 1992, Volume 12 Issue 06 Previous Issue    Next Issue
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    SAFE ZONE OF SPACE RENDEZVOUS AND MOTION TRACK OF ASTRONAUT DURING EXTRA-VEHICLE
    Lin Laixing (Beijing Institute of Control Engineering)
    1992, 12 (06):  . 
    Abstract ( 1587 )   Save
    In this paper the motion equations of the space rendezvous and their analytical solution are derived.The dynamic characteristics of the motion have been investigated. The safe zone during space rendezvous is dermined by the selection of the initial conditions.Finally,the motion track of the astronaut during extra-vehicleis discussed.
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    SATELLITE TELEMETRY DATA PROCESSING TERMINAL SOFTWARE
    Liu Hong (Beijing Institute of Spacecraft System Engineering)
    1992, 12 (06):  . 
    Abstract ( 1940 )   Save
    This paper describes the design and application of the satellite telemetry data processing terminal software. Discussion is also given on such problems as data synchro-detecting,error-control in procedure of sate- llite telemetry data acquisition and processing.
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    POSITION DETERMINATION AND DIGITAL MAP IN RDSS
    Guo Jianning (Beijing Institute of Satellite Information Engineering)
    1992, 12 (06):  . 
    Abstract ( 1606 )   Save
    The paper describes a new method to establish digital map efficiently by using contour.Data frame was designed to store digital map data.A Positioning method correspondent to the digital map was developed The position calculation was carried out in the digital map of 400km~2 area and the results illustrated that position method was simple and fast, digital map was effective and could spare the memory space.
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    A TEST OF THE ACCURACY OF CALIBRATION FOR INFRARED CHANNELS OF THE FY-1 SATELLITE
    Fan Tianxi Rong Zhiguo (Satellite Meteorological Center,SMA)
    1992, 12 (06):  . 
    Abstract ( 1513 )   Save
    Calibration is very important in application of meteorological satellite data.This paper uses a method of relative calibration to check the calibration accuracy of infrared channels for both FY-1B and NOAA-10 satellites,the results verified that their differences not exceed by±1℃.
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    THERMOELECTRIC GENERATORS FOR SPACE APPLICATIONS
    Gao Min (Kunming Institute of Physics,China) D.M.Rowe (University of Wales College of Cardiff,UK)
    1992, 12 (06):  . 
    Abstract ( 1765 )   Save
    A key subsystem for space flight and planned bases of space exploration is electrical power generation. It requires high reliability and long duration of performances. Thermoelectric conversion system has been successfully employed for this purpose in a number of missions of NASA's space programmes.In this paper,thermoelectric generators using radioiso- tope and nuclear reactor as heat sources were described and the applica- tions were listed.
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    ON DESIGN OF CARRIER SYSTEM USING AN UNGUIDED SOLID SOUNDING ROCKET
    Li Dayao (Beijing Institute of Space Machine and Electricity)
    1992, 12 (06):  . 
    Abstract ( 1759 )   Save
    The carrier system that consists of an unguided solid sounding rocket and a set of launching facilities is a part of solid rocket sounding system. The design procedure in each developing stage for this carrier system is introduced.Several principles for selection of system scheme and design method of system parameters are discussed with emphasis.
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    CHARACTER OF MATERIALS ON SATELLITE SURFACE AND CHARGE ACCUMULATION
    Lu Yusun (Lanzhou Institute of Physics,CAST)
    1992, 12 (06):  . 
    Abstract ( 1744 )   Save
    The charge accumulation on satellite surface in substorm is not avoidable.Owing to the difference in physical characteristics between sur- face materials,the accumulation of charge will not be in equilibrium.How- ever,the potential difference no sooner establishes than the exchange of charge between surface and frame of satellite begins to decrease gradual- ly. The relationship among the change of potential difference,the surface potential value,the surface conductivity and the capacitance has been de- duced by means of establishing a physical model.Thus a mathematical model can be obtained.The analysis of charging state on a satellite surface can be realized by the mathematical model.
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    MEASUREMENT OF THE MICROGRAVITY LEVELS IN 1990 CHINESE RETURNABLE SATELLITE
    Xue Datong Cao shencheng Wei Xiangrong Chen Xuekang Cheng Yufeng Zhang Shaohong (Lanzhou Institute of Physics)
    1992, 12 (06):  . 
    Abstract ( 1895 )   Save
    The constitution,function and installation of the microgravity measurement system used in the 1990 returnable satellite and the method of processing the microgravity data were introduced in this paper.It was pointed out that 4μg dynamic resolution and 6ms response time of the JS05-1A accelerometer have reached advanced world level of the same intru- ments. The application of our microgravity measurement system provided an effective means for understanding and improving the working condition of satellite.By analysising the data it was found that the working condition of the instruments was the main factor that affected the microgravity level in satellite,which is about 10~(-4)g.When major instruments turned off,the absolute value of 97.6% microgravity data was less than 4×10~(-5)g,0.3% of them was about 10~(-4)g and 1.23% of them was affected by the unknown disturbance which was over 10~(-4)g.
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    PROCESSING OF PLUMBUM-STIBUM ALLOY UNDER MICROGRAVITY ENVIRONMENT IN SPACE
    Rong Lijian Wen Youhai Zhang Xiumu Li Yiyi (Institute of Metal Research,Academia Sinica,Shenyang)
    1992, 12 (06):  . 
    Abstract ( 1678 )   Save
    Small pieces of Plumbum-Stibum (Pb-11.2wt%Sb) were sealed in quartz tube,heated and then cooled slowly during the flight of the satellite in space.And the simulating experiment is also carried out on the ground.The microstrutual feature and morphology of space processed samp- les have been investigated in comparison with ground-based samples.It was found that the space sample with smooth surface has very homogeneous and fine microstructure,while the ground-based samples,one has split into two parts and the other one has“narrow neck”in the middle.The reason for these is that the convection induced by gravity has been reduced greatly under microgravity environment in sapce.
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    DESIGN AND IMPLEMENTATION OF CAE INTEGRATED FILE MANAGEMENT SYSTEM
    Lin Baozhen Lin Hong Wang Pengju (Beijing Institute of Satellite Information Engineering) Xiao Pangang (Xian Men University)
    1992, 12 (06):  . 
    Abstract ( 1544 )   Save
    This paper presents general design ideas of CAE integrated file management system,leveled model structure,related parameters set management,integrated function module and friendly user interface.FMS can applied to other file management.
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