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    25 August 1989, Volume 9 Issue 04 Previous Issue    Next Issue
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    COMPUTER DESIGN OF DOUBLY CURVED REFLECTOR ANTENNA PATTERN
    Ye Yunshang
    1989, 9 (04):  1-12. 
    Abstract ( 1708 )   Save
    The paper describes the equations of the central vertical sectionand the transversal-strips of doubly curved reflector.It gives calculating for-mulas for far field radiation of the shaped-beam doubly curved reflector.The paper synthesizes and analyses the doubly-curved reflector by means ofcomputer.Established design-software can complete design of the shaped beamfor the doubly-curved reflector antenna,and gives all coordinate data of thereflector.
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    PLANE-BLACKBODY RADIANT SOURCES WITH HEAT PIPE
    Wen Yaopu
    1989, 9 (04):  13-19. 
    Abstract ( 1516 )   Save
    Plane-blackbody radiant sources have been designed and producedin terms of heat pipe theory in order to calibrate remote sensing instruments,such as scanning radiometers,spectrometers and thermal imaging systems.The measured results indicated an excellent temperature uniformity on therequired surfaces.In addition,the equipment is of without vibration,noiseand contamination.
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    THIN CONDUCTIVE FILMS FOR CHARGING STATE PASSIVE CONTROL ON SPACECRAFT SURFACE
    Lu Yusun Li Hua Han Xiaowen (Lanzhou Institute of Physics)
    1989, 9 (04):  20-27. 
    Abstract ( 1749 )   Save
    The concept and advantages of charging state passive control onthe spacecraft surface have been represented in this article.The indiumoxide/tin oxide film,indium oxide film and tin oxide film for the chargingstate passive control has been prepared by reacted magnetron sputtering.Thetransparence,radiant emittance and surface resistivity of the films has beengiven.The charging characteristic of the films in the simulated spaceenvironment,which contains vacuum,solar irradiation and substorm,wasalso evaluated.The results of experiments and measurements prove that theperformances of the films agree with the NASA specifications about theprevention of charging on spacecraft surface.
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    A METHOD OF BREAKING DOWN COST OF SATELLITE SYSTEM DEVELOPMENT
    Bao Miaoqin
    1989, 9 (04):  29-39. 
    Abstract ( 1740 )   Save
    This paper gives a method of breaking down the cost of satellitesystem development.Input resources and output product are taken as the basicelements of cost breaking.With these elements a matrix is established to breakand sum the total cost.Some ways of breaking down the cost estimated inpre-phase A and phase A are suggested.
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    SOME MATHEMATICAL MODELS FOR SPACE SCIENCE AND TECHNOLOGY
    Huang Liede (Tong-ji University,Shanghai)
    1989, 9 (04):  40-47. 
    Abstract ( 1533 )   Save
    The aim of this article is to consider the mathematical modelsof combustion theory for chemical rocket motors.It includes the followingparts:1.Deflagration-to-detonation transition;2.Spray evaporation;3.Erostive burning of solid rocket moters;4.Stochasic models of fatigue crack propagation;5.The formulation of dynamical equations of motion of complexspacecraft.
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    MATERIAL OF SPACE SUIT AND DEVELOPING TREND
    Lin Ziyuan (Institute of Space Medico-Engineering,Beijing)
    1989, 9 (04):  48-54. 
    Abstract ( 2152 )   Save
    In manned space flight,space suit is a essential equipment inorder to ensure astronaut's safety and his operational ability well.However,Selecting and/or developing perticular material of space suit is a key technol-ogy in the developing space suit.This paper presents a description completelyabout impact of space environment on space suit,requirement of space suitmaterial and its developing trend.
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    A CALCULATION FORMULAR OF THE POLARIZATION ALIGNMENT ANGLE OF EARTH STATION ANTENNA
    Guo Wenjia
    1989, 9 (04):  55-58+47. 
    Abstract ( 2869 )   Save
    A calculation formular of the polarization alignment angle ofearth station antenna,receiving liner polarized radiation signal from thecommunications satellites,has been given in this paper.The polarizationalignment angle of the antenna of an earth station,which operates in theliner polarized communications system,is variable upon its location.By useof coordinate transform,a pragmatical formular is produced.In the installationand adjustment of an earth station,the polarization alignment angle can beeasily calculated as far as finding out the announced longetude of the satellitelocation and bore-sight of its antenna,and the longetude and lagitude of thebeing installed station.The formular given in this paper is not only correctefor the TV receiving stations,but suitable for the communications earthstations as well.
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    STUDY OF BRAIN SUPRA-SLOW ENCEPHALOFLUCTUOGRAPH OF RABBIT DURING SIMULATED WEIGHTLESSNESS
    Shen Xianyun et al (Institute of Aerospace Medico-Engineering,Beijing)
    1989, 9 (04):  59-65. 
    Abstract ( 2406 )   Save
    The changes of brain supra-slow encephalofluctuograph ofrabbit were significant during head-down 20°suspension for 15 days.Some of16 spectra sections,the structures of S_1-S_8 specta,the S spectra harmonicoscillation and power ratio were changed.These changes indicate the brainfunction of rabbit's was influenced by the suspension.The result showedthe Brain Supra-slow Encephalofluctuograph Technology can be used tostudy the brain function of astronaut during weightlessness.
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    EFFECTS OF VACUUM AND TEMPERATURE ENVIRONMENT ON DEPLOYMENT OF SATELLITE SOLAR WING PANEL
    Li Liqiang (Beijing Institute of Environmental Test Engineering)
    1989, 9 (04):  66-71. 
    Abstract ( 1828 )   Save
    Concerning deployment of folded solar wing panel of satellite,this paper emphatically analyses the effects of the vacuum and low tempe-rature environment on deployment,based on some practical flight status ofsatellites and its simulating test data on ground in China and other countries,and emphasize the importance of deployment test at low temperature conditionin Vacuum on ground and measuring its deployment specific property.Fina-lly,this paper presents some views and recommendations on the deploymentmechanism.
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