航天探测器CO2两相主动热控系统试验及分析  

TESTING OF A MECHANICAL PUMPED TWO PHASE CO_2 COOLING SYSTEM FOR SPACE DETECTOR

作　　者：李廷勋[1] 刘杰[2] 肖文佳[1] 何振辉[1] 

机构地区：[1]中山大学,广东广州510725 [2]上海交通大学,上海200030

出　　处：《工程热物理学报》2009年第2期199-201,共3页Journal of Engineering Thermophysics

基　　金：广东省人民政府科技专项、科技部国际科技合作重点项目计划(No．2003DF000050);广东省自然科学基金项目(No．05003274);973计划前期研究专项(No．2006CB708613)

摘　　要：本文设计了一种以机械泵驱动的CO_2两相散热系统,用于高热流密度航天探测器的高精度温度控制。分别对其稳态特性包括散热热流密度、流动阻力特性和动态性能包括启动特性、控温特性试验研究发现:机械泵CO_2两相控温系统控温精度不低于1.5℃,启动性能和控温实时性能良好。In the paper, a prototype of mechanical pumped two phase CO2 cooling system was designed and built, which could be used for high accuracy thermal control for space detector with high heat load. Static characters of the system like cooling capacity and hydraulic were tested. Dynamic tests including start-up and temperature control were also performed. It was found that the mechanical pumped two phase CO2 cooling systems could start-up smoothly and control the temperature stably. The temperature variation is less than 1.5℃.

关 键 词：CO2 两相 控温 航天 

分 类 号：TB61[一般工业技术—制冷工程]