不同真空度下多层隔热组件传热性能的实验研究  

Experiment research on heat-transfer capability of the multi-layer insulation blankets under different vacuum degrees

作　　者：陈阳[1] 宁献文[1] 苏生[1] 张冰强[1] 张栋[1] 郑凯[1] 马巨印[1] 高庆华[2] 张杨[1] 

机构地区：[1]北京空间飞行器总体设计部,空间热控技术北京市重点实验室,北京100094 [2]北京卫星环境工程研究所,北京100094

出　　处：《中国科学：技术科学》2015年第3期263-267,共5页Scientia Sinica(Technologica)

基　　金：国家中长期科技发展规划重大专项资助项目

摘　　要：针对月地高速再入返回飞行器在轨面临长期中真空环境的特殊挑战,热控设计需要评估不同真空度下多层隔热组件的传热性能差异.采用一维绝热型边界测试方法,对5单元、10单元、15单元与20单元多层隔热组件,在0.001-10000 Pa开展了传热性能的实验研究.根据测试数据,计算了不同真空度下的当量导热系数,在整器热分析模型中优选当量导热系数来计算整器温度水平,并利用正样热平衡试验和在轨温度遥测值验证了该方法的正确性.本文的测试结果不仅可为返回器提供基础数据,还可成为多层隔热组件不同真空条件下航天器热设计、热分析的重要依据.The high-speed reentry capsule of lunar spacecraft will face a weak vacuum environment long-term on orbit, thus the difference of heat-transfer capability of the multi-layer insulation blankets under different vacuum degrees should be evaluated in thermal design. In this article, an one-dimensional method of mesurement with adiabatic boundary condition was constucted to test the heat tranfer performance of multi-layer insulation blankets with 5, 10, 15 and 20 under 0.001-10000 Pa. Based on the test data, equivalent thermal conductivities of different vacuum degrees were calculated. The proper equivalent thermal conductivity is selected in the entire spacecraft thermal analyses, and this method is proved to be correct through thermal balance test and on orbit temperature telemetry. This work achieves not only basic data for reentry capsule, but also important fundation of thermal design and thermal analyse with multi-layer insultaion blankets in different vacuum degree.

关 键 词：多层隔热组件 真空度 传热性能 热控设计 当量导热系数 

分 类 号：V416[航空宇航科学与技术—航空宇航推进理论与工程]