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

被引：0
|
作者：
Liu Qingzhi [1 ,2 ]
Yang Changpeng [1 ,2 ]
Xu Kan [1 ,2 ]
Zhao Xin [1 ,2 ]
机构：
[1] Beijing Inst Spacecraft Syst Engn, Beijing 100094, Peoples R China
[2] Beijing Key Lab Space Thermal Control Technol, Beijing 100094, Peoples R China
来源：
CHINESE SPACE SCIENCE AND TECHNOLOGY | 2023年 / 43卷 / 04期
关键词：
high power source; two-phase loop; system simulation; excess drive capacity; heat transfer performance;
D O I：
10.16708/j.cnki.1000-758X.2023.0058
中图分类号：
V [航空、航天];
学科分类号：
08 ; 0825 ;
摘要：
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.
引用
收藏
页码：104 / 110
页数：7
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