应用可展开辐射器的大功率卫星热设计与验证  

Thermal Design and Test of High Power Satellite with Deployable Radiator

作　　者：刘庆志[1] 黄磊[1] 任红艳[1] 高宇纯 郑红阳 杨敏 LIU Qingzhi;HUANG Lei;REN Hongyan;GAO Yuchun;ZHENG Hongyang;YANG Min(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,北京100094

出　　处：《航天器工程》2022年第4期54-58,共5页Spacecraft Engineering

摘　　要：为解决大功率卫星热排散难题,针对卫星布局特点,提出了组合式可展开辐射器热设计方法,并利用单相流体回路实现了热源与3台独立可展开辐射器之间的高效耦合。开展了整星地面热平衡试验,对卫星热排散能力进行了验证。结果表明:采用组合式可展开辐射器后,卫星长期热排散能力由1500 W提高至3000 W以上,短期热排散能力达到6500 W。大功率热排散设计方法可为空间类似任务提供参考。A thermal design method of combined deployable radiators based on satellite configuration is presented to overcome heat dissipation difficulty of high power satellite.Three deployable radiators are developed and thermally coupled with single-phase fluid loop.Heat dissipation capability of the satellite is verified by ground thermal balance test.Results show that long-term heat dissipation is increased from 1500 watts to 3000 watts and short-term heat dissipation is increased to 6500 watts with combined deployable radiators.The thermal design method of high power satellite can be referenced by similar space tasks.

关 键 词：可展开辐射器 大功率卫星 热平衡试验 

分 类 号：V416.5[航空宇航科学与技术—航空宇航推进理论与工程]