航天飞行器典型高温透波结构热匹配性能分析

The Analysis of Thermal Matching of a Typical High Temperature Wave Transmission Structure of Aero-Spacecraft

针对一种航天飞行器典型天线窗类高温透波结构及其安装形式,通过Abaqus有限元仿真分析方法对其热匹配特性进行了研究。研究表明:天线窗结构热匹配产生的热应力主要与金属壳体受热膨胀有关,石英纤维增强二氧化硅天线窗具有更优越的热匹配性能,天线窗直径越小,厚度尺寸越大,热应力越小,热匹配性能越好。该项研究为典型天线窗类高温透波结构在航天飞行器上的应用提供了参考。

Aimed at a typical high temperature antenna window wave transmission structure of aero-spacecraft,this paper carried out the research on analysis of structure thermal matching using finite element analysis by Abaqus.The research shows that the thermal stress due to the thermal matching of antenna window is mainly related to the thermal expansion of the metal shell of aero-spacecraft.Quartz fiber reinforcement silicon dioxide has superior thermal matching performance.When the diameter of antenna window is smaller and the thickness is bigger,the thermal stress would be smaller and the performance of thermal matching more superior.This paper provides reference to the application of antenna window wave transmission structure in aero-spacecraft.