摘要
根据高分辨率卫星上星敏感器的特点和任务需求，通过仿真分析与试验相结合的方法对星敏感器组件进行热设计。首先，根据热变形分析确定星敏感器支架的热控指标为18±3℃。其次，根据轨道参数及结构布局获得3只星敏感器及其安装支架的外热流，同时考虑内热源分布及多层隔热材料表面参数的退化等因素，选用被动热控和主动热控相结合的热控模式。然后，通过仿真分析，得到星敏感器支架在低温工况和高温工况下的温度范围为17.0~19.1℃。最后，通过热平衡试验及在轨温度测试验证热设计，星敏支架在各试验工况下的温度范围为17.3~18.7℃，与分析结果相符；在轨测试星敏支架的温度范围为16.0~19.0℃，满足热控指标要求18＆#177;3℃。热设计合理有效，满足任务需求。
Based on the structure character and mission requirements of star sensors used by high detectivity satellites, thermal design of star sensor assembly was accomplished by combining thermal simulation analysis and thermal balance test. Firstly, the temperature target of the bracket of the star sensors was determined by the thermal transformation analysis. Then according to the orbit parameters and the positions of star sensors, the incident space heat fluxes of three star sensors were computed. Besides the fluxes, internal heat sources of star sensors and degradation of MLI were also considered to complete the design. Both the passive thermal control and the active thermal control were applied. The simulation analysis indicates that the temperatures of the assembly was between 17.0℃ to 19.1℃. Finally, the thermal design was examined by thermal balance test and temperature test in orbit. The results of thermal balance test show that the temperatures of the assembly are between 17.3℃ to 18.7℃ and the remote data show that the temperatures are between 16.0℃ to 19.1℃. Both the data indicate that the temperatures of the assembly are between 18℃＆#177;3℃and the thermal design is valid and reasonable which can＆amp;nbsp;meet the mission requirements.
出处
《红外与激光工程》
EI
CSCD
北大核心
2014年第11期3740-3745,共6页
Infrared and Laser Engineering
基金
国家863计划(2008AA121803)
关键词
星敏感器
热设计
热仿真分析
热平衡试验
star sensor
thermal design
thermal simulation analysis
thermal balance test
