轨道再入飞行器气动热力学环境研究

 高超声速飞行器气动热力学环境研究是直接涉及轨道飞行器飞行控制、热防护设计和热安全的关键问题之一。本文借助于多组分、考虑非平衡态气体的振动以及激波与热化学非平衡态效应的守恒积分型Navier-Stokes方程组，使用高分辨率总变差减小格式，计算研究了轨道再入飞行器再入地球大气层的10个飞行工况（飞行马赫数9.7～27.8），分析了不同工况下轨道再入飞行器弓形脱体激波后流场气动热力学环境特性，得出气动力系数和沿壁面的热流密度分布，与国外相关飞行数据比较，两者吻合较好。

Aerothermodynamics Environments of Orbital Return Vehicle

The thermochemical nonequilibrium, aerodynamic heating and aerodynamic characteristics of the hypersonic vehicle flow field are important issues in computational fluid dynamics. In typical space shuttles, during return capsule re-entrying the Earth's atmosphere, or in the process of a variety of probes entering the atmosphere of other planets, the effects of gas molecules in high-temperature flow field behind the shock wave, such as vibration excitation, dissociation, ionization and thermal radiation, are significant, because of the very high speed of vehicle, which would affect the flow field in the state of flow and thermodynamic properties. Analytical study of aerothermodynamics is an important part in the flight control and the vehicle Thermal Protection System (TPS) design. The flow fields of the Orbital Return Vehicle (ORV) aviating in the earth atmosphere with the Mach number varying from 9.7 to 27.8 were simulated in 10 cases by using the conservation integral form of Navier-Stokes equations with multi-species, nonequilibrium molecular thermal excitation and chemical reactions, based on the high-resolution Total Variation Diminishing (TVD) scheme. Aerodynamics and heat transfer of the high-temperature and high-velocity flow field behind bow shock were studied, and the aerodynamics coefficient and the wall heat flux are in good agreement with fight data. This study provides some useful data for designing vehicles' TPS.