摘要
为了保证应用平台在轨任务期间的星敏感器正常工作,需要对其进行热设计。结合微型星敏感器组件的空间环境外热流、安装布局以及工作模式等条件,在热分析优化的流程上考虑了光机热等多种因素影响,设计了微型星敏感器组件的热控方案。该热控方案提出采用主动电加热以及遮光罩与星敏本体均温化的设计思路,解决了微型星敏感器组件在轨期间的空间热环境复杂、温度控制要求高、散热途径受限于安装结构等问题,保障了微型星敏感器组件有效、可靠的工作。建立了I-DEAS/TMG有限元分析模型,开展了高、低温工况下的星敏感器组件的热控仿真,分析了星敏感器组件的温度分布以及均匀性等仿真结果,最后进行了地面试验,验证了热控方案的正确性,满足星敏感器组件热设计要求。文中工作可为后续在轨平台的微型星敏热设计提供参考。
In order to ensure the normal operation of the star sensor during the on-orbit mission of the application platform,it needs to be thermally designed.First,a process of thermal analysis and optimization was proposed,which combined with the conditions of the external heat flow,installation layout and working mode of the micro star sensor assembly.In the process of thermal analysis optimization,the influence of various factors,such as optical,mechanical and thermal,was considered.Second,a thermal control scheme of the micro star sensor assembly was designed.The thermal control scheme proposed a design idea of using active electric heating and homogenizing the temperature between the light-shield and the star sensor body,which solved the problems of complex space thermal environment,higher temperature control requirements,and heat dissipation path limited by a installation structure during the on-orbit period of the micro star sensor module.This scheme ensured the effective and reliable work of the micro star sensor assembly.Third,an I-DEAS/TMG finite element mode was established.The thermal control simulation of the micro star sensor assembly under high and low temperature conditions was carried out,and the simulation results of the temperature distribution and uniformity of the star sensor assembly were analyzed.Finally,a ground test was carried out to ensure the correctness of the thermal control scheme,and the test results met the thermal requirement of the star sensor assembly.This paper can provide a reference for the following thermal design of micro star sensor assembly of on-orbit platforms.
作者
吕建伟
王领华
苏生
宋馨
刘欣
宋博旸
Lv Jianwei;Wang Linghua;Su Sheng;Song Xin;Liu Xin;Song Boyang(China Academy of Launch Vehicle Technology,Beijing 100076,China;Beijing Institute of Spacecraft System Engineering,Beijing 100094,China;Capital Aerospace Machinery Corporation Limited,Beijing 100076,China)
出处
《红外与激光工程》
EI
CSCD
北大核心
2022年第11期257-262,共6页
Infrared and Laser Engineering
关键词
热设计
热分析
微型星敏
thermal control design
thermal analysis
micro starsensor
