多部件热真空试验用冷板研究(英文)  

Study on cold plate applied for multi-subassembly thermal vacuum test

作　　者：张葆森[1] 裴一飞[1] 孙洪进[1] 陈金明[1] 

机构地区：[1]北京卫星环境工程研究所,北京100094

出　　处：《航天器环境工程》2009年第6期519-522,共4页Spacecraft Environment Engineering

摘　　要：在航天器部组件热真空试验中,当两个试件在同一个空间环境模拟器内试验时,应防止两者之间的热影响。由于试件本身的热性能参数和试验可能要求不同,减少这种影响的有效措施就是将两个试件用液氮冷板隔开,这就要求在试验中冷板的温度必须与热沉基本一致。文章通过对适合做冷板的结构进行有限元分析,设计了一种新型的液氮冷板,能够将两个试件之间的热影响降低到很小。试验结果表明,这种结构的冷板能适应热真空试验的各种工况。In the thermal vacuum test for spacecraft subassembly,when two specimens are tested in a same space environment simulator,the mutual temperature influence between them due to the difference of their thermophysical property and test requirements should be avoided.An effective method to reduce this influence is to separate them by using a cold plate,which requires that its temperature must be consistent with the heat sink of the space environment simulator in the test.In this paper,a new type of cold plate is designed,based on the finite element analysis of the finned pipe,which can reduce the influence to the smallest degree.The test results indicate that this type of clapboard can be adapted to various cases in the thermal vacuum test.

关 键 词：多部件 热真空试验 冷板 有限元分析 

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]