倾斜轨道星敏感器热控设计及在轨分析  

Thermal Design and On-orbit Thermal Analysis on Star Sensor of Inclined-orbit Satellite

作　　者：杨昌鹏[1] 赵欣[1] 辛强[2] 

机构地区：[1]北京空间飞行器总体设计部空间热控技术北京市重点实验室,北京100094 [2]航天东方红卫星有限公司,北京100094

出　　处：《航天器工程》2013年第6期59-64,共6页Spacecraft Engineering

摘　　要：倾斜轨道卫星星敏感器空间外热流复杂多变,同时兼具内功率集中、热容小等特点,这为星敏感器的热设计带来了很大的困难。文章以某临界倾角轨道卫星星敏感器热设计为背景,在详细外热流分析的基础上,提出了一种倾斜轨道星敏感器热设计方案,利用热分析软件Thermal Desktop对此热控系统进行了具体的热分析。星敏感器在轨遥测温度在-19.8^-5.1℃之间,满足温度指标要求,表明星敏感器热设计合理、有效,可为今后倾斜轨道星敏感器热设计提供设计依据。在此基础上,文章利用在轨遥测数据对星敏感器热分析模型进行修正,得出入轨初期星表主要热控涂层退化约为50%的结果,这对于分析近地轨道卫星在轨温度具有一定的参考意义。Inclined-orbit satellite star sensor has both varying orbital heat flux and complex charaeteristics such as concentrated internal power, small heat capacity, which bring a lot of dif- ficulties in star sensor thermal design. Taking a star sensor thermal design of a critical inclined- orbit satellite an example, this paper presents an inclined-orbit satellite star sensor thermal control design method based on detailed analysis of orbital heat flux, and carries out a detailed thermal analysis by using thermal analysis software Thermal Desktop for this system. On-orbit telemetry temperature of the star sensor is between -19.8℃ and -5.1℃, which satisfies the temperature requirement very well and shows the method is reasonable and effective. This method provides a design basis for the future inclined-orbit satellite star sensor thermal design. On this basis, the star sensor thermal analysis model is modified by the use of telemetry data and obtains that the initial degradation of main thermal control coatings is about 50%, which can be a reference for the analysis of low earth orbit satellite^s initial on-orbit temperature.

关 键 词：倾斜轨道 星敏感器 热设计 在轨分析 

分 类 号：V423.4[航空宇航科学与技术—飞行器设计]