嫦娥五号探测器热平衡试验方案设计与实现  

Design and implementation of thermal balance test scheme for Chang’e-5 probe

作　　者：宁献文[1] 蒋凡[1] 陈阳[1] 张栋[1] 王玉莹[1] 薛淑艳[1] NING Xianwen;JIANG Fan;CHEN Yang;ZHANG Dong;WANG Yuying;XUE Shuyan(Beijing Key Laboratory of Space Thermal Control Technology(ISSE),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,空间热控技术北京市重点实验室,北京100094

出　　处：《中国空间科学技术》2021年第6期132-137,共6页Chinese Space Science and Technology

基　　金：国家自然科学基金(11472040)。

摘　　要：针对嫦娥五号探测器热平衡试验中面临的难题,在分析以往国内外航天器热平衡试验技术现状基础上,依据验证充分、有效与全面的原则,构建出一套探测器热平衡试验方案,提出一种基于“专用红外吸收式空间外热流模拟方式”的热平衡试验方法,设计了典型试验工况,同时优化了试验技术流程。地面热平衡试验结果结合在轨飞行数据表明:热平衡试验方案能够有效验证热控设计的正确性,专用红外吸收式外热流模拟装置偏差造成的温度影响不超过2℃,热平衡试验工况设置合理,技术流程优化,热分析模型相关性工作可使热分析模型更加准确可信。Aiming at the problems faced in the thermal balance test of Chang’e-5 probe,a set of thermal balance test scheme was constructed,and a thermal balance test method was proposed based on the analysis of the current situation of thermal balance test technology of spacecraft at home and abroad,as well as the principle of full verification,effectiveness and comprehensiveness.A special infrared absorption space heat flux simulation method was used.The typical test conditions were designed,and the test technical process was optimized.The results of thermal balance test combined with on-orbit flight show that the thermal balance test scheme can effectively verify the correctness of thermal control design,that the temperature impact caused by the deviation of the space heat flux simulation device does not exceed 2℃,and that the setting of test conditions and the technical process is reasonable.The correlation of thermal analysis model can make the thermal analytical model more accurate and reliable.

关 键 词：嫦娥五号 热控 热设计 热平衡 空间外热流 

分 类 号：V19[航空宇航科学与技术—人机与环境工程]