高超声速多体分离过程气动加热计算技术

摘要

In this paper,a method of aerodynamic heating prediction for hypersonic multi-body separa-tion process is presented.The inviscid outflow solution during multi-body separation and the engineering method for aerodynamic heating are combined,and then the structure heating coupling effect is considered to calculate the temperature distribution of thermal protection systems.For assumed layout of multi-body sepa-ration aircraft,this method accomplishes the calculation of temperature distribution characteristics and heat flux distribution characteristics during the separation,and analyses the influence of multi-body separation on aerodynamic heating.The research results show that the computing technology developed in this paper can provide technical support for hypersonic aircraft design both on the thermal protection systems and aerody-namic heating characteristics analysis.%发展了无粘外流解与气动热工程方法相结合的用于全机外形复杂流动气动加热计算技术，并将其与动态多体分离过程流场解相结合，提出了一种高超声速飞行器多体分离过程气动加热特性计算技术，然后耦合结构传热，实现了飞行器热防护系统中结构材料温度分布特性的数值模拟。采用本文方法，针对假定高超声速多体分离布局及飞行条件开展了分离过程中的结构温度分布特性与热流密度分布特性计算，分析并给出了组合体分离过程中部件干扰对气动热的影响特性。结果表明本文发展的计算技术可为高超声速飞行器的防热方案设计、气动热特性定性分析及热防护系统设计等提供技术支持。