航天器多层隔热材料边缘漏热分析与设计  

Analysis and Design of Edge Heat Leakage from Spacecraft Multilayer Insulation

作　　者：戴勇超[1] 王新升[1] 黄海[1] 郭静[1] 

机构地区：[1]北京航空航天大学宇航学院,北京100191

出　　处：《宇航学报》2014年第1期76-82,共7页Journal of Astronautics

基　　金：CAST创新基金(CAST20100604)

摘　　要：推导了高真空多层隔热材料(MLI)的一维传热半经验公式,结合文献实验数据反演了屏间固体导热系数和反射屏发射率。以此为基础,采用有限元方法建立了多层隔热组件的二维稳态辐射和导热的复合传热数值分析模型。定量分析了影响隔热性能的多个因素(如安装面积、层密度、压敏胶带的导热系数和发射率)对边缘漏热的影响。比较了多层隔热材料周边不包覆和进行包覆两种情况下的边缘漏热大小,得到了对周边进行包覆时的漏热量比不封闭情况下的漏热量更大的结论,并给出了减小边缘漏热的设计。本文的分析结果能够为多层隔热组件的优化设计提供一定依据。The edge heat leakage will generate if the shields in multilayer insulation （MLI） can＇t form a closed system, thus producing certain effect on the performance of heat insulation. The two dimensional steady state and combined radiation/conduction heat transfer in MLI is modeled by using the finite element method to simulate the thermal loss from edge of MLI. The effects of design parameters such as mounting area, layer density, thermal conductivity and emissivity of pressure-sensitive tape on the edge heat leakage are analyzed. Two cases that whether the boundary of MLI is covered or not are compared to decide which one is better in heat insulation. Based on the analysis results some useful designs that help to reduce thermal loss from edge of MLI are proposed.

关 键 词：多层隔热 边缘漏热 航天器 复合传热 

分 类 号：V444.3[航空宇航科学与技术—飞行器设计]