立尾热-力耦合计算分析方法

Calculation Analysis Method of Thermal-mechanical Coupling of Vertical Tail

在航天飞行器设计过程中,为了保证立尾设计的安全可靠,针对立尾开展热-力耦合的计算分析。通过ABAUQS商业有限元计算软件,建立立尾有限元网格模型,对其施加修正的热流和约束条件,利用顺序耦合方式计算出立尾在整个飞行过程中的瞬态温度场、热-力耦合条件下的应力分布和位移,全面介绍立尾热-力耦合计算分析方法。该方法可分析大气层内热-力耦合环境对飞行器热防护系统的热-力响应,为相关飞行器设计提供了可靠技术手段。

In the design process of the spacecraft,in order to ensure the safety and reliability of the design of the vertical tail,the calculation and analysis of the thermal-mechanical coupling is carried out for the vertical tail.Through the ABAUQS commercial finite element calculation software,a vertical finite element mesh model is established,and modified heat flow and constraint conditions are applied to it.The sequential coupling method is used to calculate the vertical temperature field and the stress distribution and displacement under the thermal-mechanical coupling conditions of the vertical tail during the entire flight process.A comprehensive analysis method of the vertical tail thermal-mechanical coupling calculation is introduced.This method can analyze the thermal-mechanical response of the thermo-mechanical coupling environment in the atmosphere to the aircraft's thermal protection system,and provides a reliable technical means for the design of related aircraft.