Table of Content

25 December 1993, Volume 13 Issue 06 Previous Issue    Next Issue

For Selected:

Download Citations EndNote Reference Manager ProCite BibTeX RefWorks

Toggle Thumbnails

Select

TIME SUBOPTIMAL FEEDBACK CONTROL OF FLEXIBLE SPACECRAFT DURING A LARGE ANGLE MANEUVER Jing Wuxing Yang Di Wu Yaohua Huang Jianjun (Harbin Institute of Technology) 1993, 13 (06):  1-7+21.  Abstract ( 1732 )   Save Feedback control of attitude maneuvers for a flexible space-craft is studied.A time suboptimal feedback control law is presented.Variable torque levels are adopted for vibration suppression.A numericalexample for a large-angle maneuver is given to illustrate effectivenessof the control law. Related Articles | Metrics

Select

THERMAL PROTECTION AND THERMAL RESPONSE OF SELF-ADAPTIVE MULTI-LAYER STRUCTURE Wang Shuhua Mao Guoliang Jiang Guiqing (Beijing Institute of Aerodynamics) 1993, 13 (06):  8-15.  Abstract ( 1917 )   Save A new concept of self-adaptive multi-layer structure waspresented.The thermal protection material of silicone is an elementalmaterial with self-adaptive multi-layer structure.The production mecha-nism of multi-layer structure for silicone at aerodynamic heating wasdiscussed,according to the experimental results.Numerical simulation ofthermal response for multi-layer structure was presented.The numericalresults were consistent with experimental results on are jet test equip-ment. Related Articles | Metrics

Select

EXPERIMENTAL METHOD OF HEAT ANALOGY USING REDUCED HEAT LOAD FOR RADIATIVE THERMAL EXCHANGE SPACECRAFT SYSTEM Li Dayao (Beijing Institute of Space Machine and Electricity) Li Dazhi (Nantong Medical College) 1993, 13 (06):  16-21.  Abstract ( 1620 )   Save The asymptotical characteristic of temperature field for theradiative thermal exchange spacecraft system in the condition of constantheat sources is discussed first.Then,according this result,the experi-mental method of heat analogy that uses the reduced heat load for abovesystem is given. Related Articles | Metrics

Select

INFORMATION ACQUISITION AND TRANSMISSION OF SPACEBORNE IMAGING SPECTROMETRY Zhang Fu (Shanghai Shiner Optoelectronics Company,Shanghai Institute of Mechanical Engineering) 1993, 13 (06):  22-27.  Abstract ( 1916 )   Save In spaceborne imaging spectrometry,the most basic andcrucial problem is information acquisition.This paper points out four keyproblems on the information acquisition technology,and emphaticallyanalyses the spectrum and radiation calibration techniques of spaceborneimaging spectrometer.Meanwhile the information transmission techniques ofspaceborne imaging spectrometry,such as overcoming satellite-to-groundtransmitting data crowding etc.,are also described. Related Articles | Metrics

Select

ECONOMIC ANALYSIS OF MOBILE COMMUNICATION SATELITES Zhu Yilin (Chinese Academy of Space Technology) 1993, 13 (06):  28-35.  Abstract ( 2269 )   Save Mobile communication service implemented by a constellationcomposed of small LEO satellites is a primary trend of development of satellitecommunication.Either of the uses of LEO and GEO satellite constellations formobile communication service has its own strong and weak points.This paperanalyses and compares the two satellite constellations in view of economics withemphasis on cost of space segments,i.e.the development cost of satellites andtheir launch cost,gives the specific calculation formula and results,and finallyconcludes that the lower the orbit height is,the higher the total cost is,andthe cost of GEO satellite constellation is the lowest.But not only its economicsbut also its effects on promoting technology must be considered in decisionmaking on whether or not the LEO communication satellite network need to bedeveloped. Related Articles | Metrics

Select

DEVELOPMENT OF EXPERIMENTAL PROTOTYPE OF 4-FEEDS SHAPED-BEAM ANTENNA IN Ku-BAND Bu Binlong Zhong Ying Yi Nianxue Ling Minhe (Xi'an Institute of Space Radio Technology) 1993, 13 (06):  36-42.  Abstract ( 1973 )   Save The basic foundation and restriction for design of 4-feedsshaped-beam antenna in Ku-band are briefly introduced.Then it emphasizeson the electrical property of antenna system and design method of crucialcomponents.By comparing preexpected results with the tested ones,goodagreement is obtained,it shows that the experimental prototype of 4-feedsshaped-beam antenna in Ku-band,we have developed recently is successful.Finally,future ideas of EM development are presented. Related Articles | Metrics

Select

DESIGN OF AIRBORNE INFRARED SCANNER Gu Mingli (Beijing Institute of Space Machine and Electricity) 1993, 13 (06):  43-52.  Abstract ( 1775 )   Save This paper describes the design and main performance parametersof the airborne infrared scanner.The dsign methods and parameter calculationsof the optics,electronics and photograph record system are described in detail. Related Articles | Metrics

Select

A DEPLOYMENT MECHANISM FOR POLAR SENSITIVE REFLECTOR Song Jianming Feng Dawu Tang Dexiao (Xi'an Institute of Space Radio Technology) 1993, 13 (06):  53-57+65.  Abstract ( 2029 )   Save The deployment mechanism is comprised of a speed regulatorand a pair of hinges in which there are a spring motor and a latch foreach.The spring motor provides energy for deployment.The speed regulatorproduces damping to stabilize the deployment speed so as not to over shockat the movement termination.Qualification tests have been accomplished.No damage was appeared after vibration test and thermo-vacuum test.Thedeployment speed at 52.3℃ in vacuum is 14% higher than that at -20℃.A deployment repeatibility of 1 are minute was detected on a zero-G device.An estimation of the impact of some factors to deployment speed wasperformed with a calculation program. Related Articles | Metrics

Select

CALCULATION OF ORBITAL PARAMETERS Ψ__0,Ω_0 AND ω_0 USED FOR CALCULATING SPACE HEAT FLUX Li Wanlin (Beijing Institute of Spacecraft Systems Engineering) 1993, 13 (06):  58-61.  Abstract ( 1664 )   Save This paper presents the formula of the initial values of theorbital parameters—celestial longitude φ_0 of the sun,right ascension ofascending node Ω_0 and argument of perigee ω_0,used for calculating orbitalheat flux received by satellite.The accuracy of calculation of these para-meters has met the requirements of thermal analysis of a satellite. Related Articles | Metrics

Select

THE SATELLITE FLYING TEST OF SECONDARY SURFACE MIRROR Qian Shengyu (Beijing Institute of Spacecraft Systems Engineering) Wang Shaohong Qiu Jiawen Chang Tianhai Hu Bingsen (Lanzhou Institute of Physics) 1993, 13 (06):  62-65.  Abstract ( 1951 )   Save In this paper,the satellite test results of the fused silicasecondary surface mirror (OSR) developed by Lanzhou Institute of Physicshave been reported,and the long-term space stability of OSR has beenestimated.the results of the test and the calculation showed that the 10-yearvariation of solar absorptance of OSR is below 0.05,with the same levelas the foreign products.It can meet the demand of satellite application. Related Articles | Metrics