Calculating method of aerodynamic heating for hypersonic multi-body separation process

In this paper, a method of aerodynamic heating prediction for hypersonic multi-body separation 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 separation 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 aerodynamic heating characteristics analysis.