论文部分内容阅读
再入返回式航天器飞行过程中,在轨温度交变环境下防热结构胶接热应力一直是航天器可靠性设计的关注內容恼乱浴爸忻芏确廊炔牧?硅橡胶-金属“的胶接结构作为对象,针对典型的低地球轨道温度交变环境,选取±100℃/5个循环环境作为分析条件,用ANSYSWorkbench建立了结构有限元分析模型,考察了不同胶层厚度对于结构热应力及热变形的影响。基于有限元计算结果、热应力理论及胶接工艺分析,给出了温度交变环境下防热结构的胶层厚度设计结果.该有限元模型分析方法可为防热结构热匹配特性研究和设计提供基础依据。
During the reentry and return spacecraft flight, the thermal stress of heat-resistant structural adhesives in the temperature-changing environment of the rail has always been the focus of spacecraft reliability design. ”For the typical low earth orbit temperature alternating environment, select ± 100 ℃ / 5 cycles as the analysis conditions, the use of ANSYSWorkbench established a structural finite element analysis model, investigated the different thickness of the adhesive layer for Structure thermal stress and thermal deformation.According to the results of finite element calculation, thermal stress theory and the analysis of the bonding process, the design results of the thickness of the thermal insulation layer under temperature alternating environment are given.The method of finite element analysis Heat-resistant structure of thermal matching characteristics of the study and design provide the basis.