航天器高稳定结构热变形分析与试验验证方法研究

航天器高稳定结构研制须探讨微米级结构热变形仿真分析与试验验证工作,以满足空间环境交变温度载荷下结构微变形要求。根据机热一体化设计的特点,提出机热一体化分析方法进行机、热载荷交互,机、热温度场交互过程由手动赋值的几天时间缩短至几分钟,且映射误差小于1℃。基于数字图像相关测量技术,采用高稳定结构微米级变形的非接触式测试方法进行试验验证。结果显示,文章中的高稳定结构在轨热变形为2~30μm。文章提出的分析与试验验证方法,可为航天器高稳定结构设计及验证提供参考。

Research on Thermal Deformation Analysis and Test Verification Method for Spacecraft High-stability Structure

In order to satisfy the requirement of micro-deformation in aerospace, the analysis and test of thermal deformation are necessary to develop the spacecraft high-stability structure. According to the mechanical thermal integrated design, a mechanical thermal integrated analysis method is introduced. From several days to just several minutes, the time needed for mapping temperature between mechanical analysis and thermal analysis is reduced significantly, and map- ping error is within 1℃. Micro-deformation measurement based on digital image correlation measurement technique is demonstrated. Results Of the thermal deformation test show that ther- mal deformation of the high-stability structure introduced in this paper is 2~30μm. The method of analysis and verification can play an important role in high-stability structure design.