航天器舱内星敏感器简化热分析方法及在轨验证  

Simplified Thermal Analysis Method and In-orbit Verification for Star Sensor in Spacecraft Cabins

作　　者：潘维[1] 罗强[1] 斯东波[1] 钟奇[1] PAN Wei;LUO Qiang;SI Dongbo;ZHONG Qi(National Key Laboratory of Spacecraft Thermal Control,Beijing Institute of Spacecraft System Engineering,Beijing 100094,China)

机构地区：[1]北京空间飞行器总体设计部航天器热控全国重点实验室,北京100094

出　　处：《航天器工程》2023年第6期84-88,共5页Spacecraft Engineering

摘　　要：一般返回类航天器的星敏感器安装于舱内,通过光窗实现在轨应用。安装于舱内的星敏感器在轨热仿真鲜有人研究,舱内与舱外星敏感器的热仿真边界不同,且需要考虑安装于航天器舱板上的光窗对星敏感器计算温度的影响。文章提出舱内星敏感器的热仿真简化处理方法,即利用局部精细模型准确求解透过光窗到达星敏感器各个位置上的外热流,再配合整器热模型准确求解舱内星敏感器温度,不需要修改整器热模型,保证航天器研制进度的同时,实现了星敏感器在轨温度的精确仿真。分析结果与在轨飞行温度数据比对后一致性良好,可为舱内星敏感器在轨热分析提供工程借鉴。As for reentry special vehicle,star sensor is installed inside the cabin and used in orbit through optical window which is integrated in spacecraft module panel.Almost no thermal analysis research has been performed on star sensor installed inside the spacecraft at present.The thermal simulation boundaries of inside and outside the spacecraft are different,and it is necessary to consider the influence of optical window installed on the spacecraft’s cabin panel on the calculated temperature of star sensor.Simplified analysis method is promoted in this paper without modifying the whole spacecraft thermal network model,it uses a local fine model to solve the orbital heat flux through optical window,then combines these output orbital heat flux into the integrated model and get accurate temperature of star sensor in the cabin.The consistency between the analysis results and in orbit temperature data is satisfied,providing a new engineering reference for thermal analysis of star sensor inside the cabin.

关 键 词：舱内 星敏感器 热分析 

分 类 号：V423.4[航空宇航科学与技术—飞行器设计]