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高温气体非平衡效应及其壁面催化效应对高超声速飞行器气动热环境造成显著影响,是当前高超声速飞行器气动热环境预测和热防护设计的关键问题之一.考虑高温空气离解与电离等化学反应、气体分子热力学激发、流动中的非平衡效应和壁面催化效应,通过数值求解三维热化学非平衡Navier-Stokes方程和壁面处质量、能量平衡关系,完善了高温气体热化学非平衡流场有限催化气动热环境数值计算方法和计算程序,采用典型算例进行了考核验证.在此基础上,开展了不同条件下高超声速飞行器热化学非平衡流场气动热环境数值模拟,分析局部催化特性差异对气动热环境的影响.研究表明:所建立的高超声速飞行器热化学非平衡流场有限催化气动热环境数值计算方法及程序,其数值模拟结果与飞行试验、文献符合;局部催化特性差异会导致热流跳变,其热流跳变量与催化特性差异量、材料分布方式等有关;催化特性差异较大时,局部区域热流可能远远高于飞行器全表面完全催化的热流结果,此时将飞行器在全表面完全催化(FCW)和完全非催化(NCW)条件下的数值模拟结果作为实际飞行过程中表面热流的上、下限这一简化处理方式,是不可取的.“,”The influence of aero-thermal environment of hypersonic vehicle because of high temperature air non-equilibrium effect and the catalytic effect has been one of the critical problems in aero-thermal environment prediction and hypersonic vehicle design.Considering the chemical reaction of the high temperature air,vibrational excitation of gas molecules,non-equilibrium effects in the flow and the catalytic effect on the vehicle surface,numerical simulation method and the corresponding computational codes are developed for the aero-thermal environment of thermo-chemical non-equilibrium flow by solving 3D thermochemical non-equilibrium Navier-Stokes equations and the balance between the mass and energy on the vehicle surface.The numerical results of the typical examples agree well with foreign reference data and flight data.On this basis,the influence of differences in local catalytic properties on the aero-thermal environment of the hypersonic vehicle under different conditions is studied.These results show that the differences in local catalytic properties can obviously lead to the jump of the heat flux.When the difference between local catalytic properties is lager,the local heat flux is far higher than the result under the fully catalytic wall condition of the whole vehicle surface,and the simplified approach of using the heat flux under the whole vehicle surface Fully Catalytic Wall (FCW) and Non-Catalytic Wall (NCW) conditions as its bounds for the actual fight is not advisable.