卫星电源分系统设备整星热平衡试验评估分析  

The Result Evaluation of Electrical Power Subsystem Equipment Attend Satellite Thermal Balance Test

作　　者：姜东升[1] 朴海国[2] 张璟[2] 王超[1] 夏宁[1] JIANG Dong-sheng;PIAO Hai-guo;ZHANG Jing;WANG Chao;XIA Ning(Beijing Institute of Spacecraft System Engineering,Beijing 100094;Shanghai Institute of Space Power-Sources,Shanghai 200237)

机构地区：[1]北京空间飞行器总体设计部,北京100094 [2]上海空间电源研究所,上海200245

出　　处：《环境技术》2025年第3期86-91,共6页Environmental Technology

摘　　要：某天文卫星电源分系统与传统低轨道卫星相比,由于整星功率增加了30%,因此电源分系统单机设备的发热量增加,为了验证单机设备与卫星热控分系统的热接口匹配,检验热设计和设备的热性能,确保各单机设备在轨工作各模式下工作温度满足建造规范要求,特利用整星热平衡试验开展电源分系统设备在空间热环境影响下的性能和温度特性测试。通过对参加试验设备温度数据趋势的分析,得出结论电源分系统设备热设计满足空间热环境影响要求。Comparing with the traditional low orbit satellite,an astronomical satellite has more heat generated by the equipment of the electrical power subsystem because the total power of satellite increasing 30%.Electrical power subsystem equipment attend satellite thermal balance test to verify the matching of heat interface between EPS equipment and thermal control subsystem under the equipment in orbit working mode and working temperature according the construction specification.According to the temperature data trend analysis of the equipment attending the test,the conclusion that the thermal design of EPS equipment satisfy the space thermal environment requirement can be draw out.

关 键 词：热平衡试验 电源分系统 温度特性 

分 类 号：V442[航空宇航科学与技术—飞行器设计]