星载大型旋转部件的热平衡试验方法  

A method of thermal balance test for space large rotating payloads

作　　者：耿利寅[1] 彭方汉[1] 王甜甜[1] 李国强[1] 孟恒辉[1] 贾宏[1] 

机构地区：[1]北京空间飞行器总体设计部,北京100094

出　　处：《航天器环境工程》2013年第3期280-285,共6页Spacecraft Environment Engineering

摘　　要：星载大型旋转部件因其构型复杂和相对星体其他部分转动的特性,给热设计的验证带来诸多难题。文章以"海洋二号"卫星的微波散射计为例,分别采用通过地面试验直接获取在轨预示温度的直接验证方法,以及验证热分析模型、再由热分析模型预示在轨温度的间接验证方法进行热平衡试验。通过对试验结果、热分析结果和在轨飞行结果的对比,验证了这2种试验方法正确、有效。Space large rotating payloads,being complex in structure and constantly rotating,are a challenge to the test validation of their thermal characteristics.A case study of the thermal balance test method of the microwave scatterometer in Haiyang-2 satellite is presented.A direct validation method is used in the engineering model phases,which can used to forecast the in-orbit temperature directly from the ground test result.Meanwhile,an indirect validation method is used in the flight-model phases,which may used to predict the in-orbit temperature through the thermal analytical model.A comparison between the thermal test results,the thermal analytical results and the flight results shows the correctness and the effectiveness of the thermal balance test.

关 键 词：旋转部件 微波散射计 热平衡试验 

分 类 号：V416[航空宇航科学与技术—航空宇航推进理论与工程]