航天器环境工程2016，Vol.33Issue(5)：516-520,5.DOI:10.3969/j.issn.1673-1379.2016.05.010
环月轨道一体式星敏感器热设计及仿真验证
Thermal designof an integrated star sensor on lunar orbit with simulation validation
摘要
Abstract
A composite design for the thermal management of an integrated star sensor on lunar orbit is proposed. On the lunar orbit, the thermal condition of the integrated star sensor is determined by the solar radiation, the infrared radiation of the lunar surface and the concentrated heat load of the star sensor. As the result, the thermal management of the star sensor is extremely difficult. The heat dissipation of the star sensor is realized through the combined actions of the heat pipe, the thermal control coating, the MLI and the electric heater. The thermal simulation is performed to verify the design. The result shows that the maximum temperature of the star sensor is 36.7℃, which satisfies the temperature requirement of the star sensor.关键词
环月轨道/月球红外辐射/一体式星敏感器/热设计/仿真分析Key words
lunar orbit/infrared radiation of lunar surface/integrated star sensor/thermal design/simulation analysis分类
航空航天引用本文复制引用
张彧,赵吉喆,张翔,刘冈云..环月轨道一体式星敏感器热设计及仿真验证[J].航天器环境工程,2016,33(5):516-520,5.基金项目
国家重大科技专项工程 （）
