中文摘要：

针对准确预测高超声速飞行器气动热环境问题，考虑高温空气化学反应效应和热力学非平衡效应，利用高超声速飞行器高温气体／非平衡效应流场计算软件（AEROPH—Flow），开展了热化学非平衡气动热数值计算，分析了高温空气化学反应模型、热力学非平衡模型、表面催化特性和表面温度对气动热环境计算结果的影响规律。研究结果表明：热化学非平衡模型对气动热的计算结果有较大影响，在气动热的数值计算中，要根据飞行环境的热化学机制或空气化学反应和非平衡效应的强弱，选择适当的空气化学反应模型和热力学模型；在高马赫数和热化学非平衡条件下，气动热数值随着表面温度的变化规律变得非常复杂，不能再认为气动热遵从随着表面温度的升高而降低的规律，表面温度最好取接近真实飞行情况的分布和不同的固定值，这样就可以找到最大的或准确的热流值。

英文摘要：

In order to design thermal protection system, it is important to predict heat transfer rate precisely on the hypersonic vehicles. In present paper, considering chemical reaction, interal energy excitation and thermo-chemical non-equilibrium effects of high temperature air, the thermo-chemical non-equilibrium flow-fields are simulated using the numerical code AEROPH_Flow. An aero-physical numerical code system for Hypersonic vehicles, the distributions of heat transfer rate is obtained, and the analysis is done for the influence of the chemical reaction model, thermodynamic non-equilibrium modeL, surface temperature, surface material catalytic action on the computational results. The results show that thermo-chemical non-equilibrium models have a more important influence on the computational results, it is important for the selection of the correct air reaction model and thermal non-equilibrium model according to the flight environment and thermo-chemical non-equilibrium mechanism of the flow-field around the hypersonic vehicles; the heat transfer rate isn＇t always the highest for lower surface temperature, and it become very complicated for the variation law of heat transfer rate along with the surface temperature under the condition of high Maeh number or thermo-chemical non-equilibrium flow, so the surface temperature may as well be fixed choosed aecording to the distribution of the real flight condition or different constant for computing exactly heat transfer rate on the hypersonic vehicles.