用于发动机羽流试验研究的液氦热沉设计  

Liquid helium heat sink design for experimental study of engine's plume and vacuum effects

作　　者：凌桂龙[1] 王文龙[1] 蔡国飙[1] 张建华[1] 

机构地区：[1]北京航空航天大学宇航学院,北京100191

出　　处：《航空动力学报》2011年第11期2630-2635,共6页Journal of Aerospace Power

基　　金：国防科工局中俄航天合作项目

摘　　要：超低温大型卧式热沉采用液氦制冷,将在国内实现热沉表面温度低于10K,主要用于航天发动机羽流效应试验,同时兼顾卫星等热真空试验.热沉主体结构为卧式圆筒型,为减小热损失,液氦热沉去掉了骨架,外部装有液氮热沉,两者采用一体化设计,液氮热沉既做液氦热沉的防辐射屏,又做液氦热沉的支撑.为增大抽速,舱体封头端设计了可拆卸的羽流吸附泵.羽流试验时液氦热沉、羽流吸附泵通液氦制冷,液氮热沉通液氮制冷,各部分热沉单独供液.对此大型热沉进行了方案设计、参数计算,对热沉预冷及稳态工况时的液氮、液氦消耗量进行了估算,分析了羽流试验时热沉抽气速率随试验工质温度的变化关系,得出液氦热沉对氮气的抽气速率可以达到107 L/s量级.The large horizontal ultra-low temperature heat sink,based on liquid helium cooling,could firstly realize heat sink surface temperature below 10 K in China,and is mainly applied to spacecraft-thruster vacuum plume effects＇ experimental study and the thermal vacuum test of satellite simultaneously.In order to minimize heat loss,the main structure of heat sink frame was removed,and the liquid helium heat sink was enclosed by a liquid nitrogen heat sink.Both of them were designed integrally so that the liquid nitrogen heat sink is not only the anti-radiation panel for liquid helium heat sink,but also the frame brace.To increase the pumping speed of heat sink,a plume adsorption pump was developed and mounted on the end of the vacuum chamber.At the experiment of vacuum plume,vacuum plume adsorption pump and liquid nitrogen heat sink were cooled by liquid helium and liquid nitrogen,respectively.The analysis was conducted for key parameters of heat sink,such as estimating the liquid nitrogen,liquid helium consumption in pre-cooling process and steady-state condition,and comparing the relationship between pumping speed of heat sink and working fluid temperature.The results show that pumping speed of the heat sink for nitrogen can reach 107 L/s magnitude.

关 键 词：真空 羽流效应 热真空试验 热沉 液氦热沉 液氮热沉 羽流吸附泵 

分 类 号：V416.8[航空宇航科学与技术—航空宇航推进理论与工程]