空间大功率热源两相温控系统设计与仿真  

Design and simulation of two-phase thermal control system for space high power source

作　　者：刘庆志[1,2] 杨昌鹏 徐侃[1,2] 赵欣 LIU Qingzhi;YANG Changpeng;XU Kan;ZHAO Xin(Beijing Institute of Spacecraft System Engineering,Beijing 100094,China;Beijing Key Laboratory of Space Thermal Control Technology,Beijing 100094,China)

机构地区：[1]北京空间飞行器总体设计部,北京100094 [2]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》2023年第4期104-110,共7页Chinese Space Science and Technology

基　　金：国家自然科学基金(11973100)。

摘　　要：为解决未来空间应用中大功率热源带来的温控问题,提出了集微槽道蒸发器、相变装置和热辐射器在内的泵驱两相流体回路热排散系统方案,在此基础上开展了系统仿真工作,对流体回路运行特性和温控能力进行了研究。仿真结果反映了大功率热源短时工作条件下两相流体回路温度、饱和压力和干度的变化特征,两相流体回路工作特性符合设计预期,60 kW分布式大功率热源峰值温度能够控制在70℃以下。对泵驱动能力过剩所带来的不利影响进行了仿真分析,得出了泵驱动能力过剩导致两相回路系统温差增大的结论。分析了蒸发器和相变装置换热性能对温控系统的影响。蒸发器换热性能降低后,热源温度将超出要求范围;相变装置换热性能降低后,泵可能受到气蚀影响。Scheme of pumped two-phase loop with micro-channel evaporator,phase change device and radiator was brought forward to solve the thermal control problem of high power source applied to spacecraft in the future.Simulation was conducted to research characteristics and thermal control capability of two-phase loop with Sinda/Fluint thermal analysis software.The results are consistent with prediction,and temperature of the heat sources is under control.The conclusion is drawn that excessive drive capacity of pump results in bigger temperature difference of two-phase loop by simulation.Effect of heat transfer capacity of evaporator and phase change device on thermal control system was analyzed and suggestions were given.

关 键 词：大功率热源 两相流体回路 系统仿真 驱动能力过剩 换热性能 

分 类 号：V416[航空宇航科学与技术—航空宇航推进理论与工程]