为了准确预测高超声速飞行器面临的严峻气动热/力环境以及结构的热力响应,发展了高超声速流动与结构传热耦合框架。采用分区求解方法,通过耦合界面的实时数据传递,实现了基于Navier-Stokes方程的高超声速化学非平衡计算流体力学(CFD)求解器与结构的热力全耦合有限元法(FEM)求解器的多场耦合计算,建立了高超声速飞行器的多场耦合数值分析方法。首先对经典高超声速圆柱绕流实验进行了耦合计算,结果与实验值吻合良好。然后针对典型的超高温陶瓷(UHTC)材料的耦合传热问题进行了数值研究,考虑热传导效应对气动热环境和结构热响应预测的影响,结果表明对于复杂外形且热导率相对较高的UHTC材料,结构内部热传导对热环境和表面温度分布的影响不可忽略。最后针对UHTC材料热物性(比热和热导率)非线性对高超声速流动传热过程的影响进行了研究,结果表明当比热和热导率处于合理的误差范围内时,材料表面温度响应对其变化并不敏感。 In order to accurately predict the severe aerodynamic heat / force environment and thermal response of hypersonic vehicles, a hypersonic flow and structural heat transfer coupling framework has been developed. By using the partition method and the real-time data transfer of the coupled interface, the multi-element FEM solver with hypersonic chemical-disequilibrium CFD solver and structure based on the Navier-Stokes equations is realized Field coupling calculation, the establishment of hypersonic vehicle multi-field coupled numerical analysis. First of all, the classical hypersonic circular flow around the cylinder was calculated and the results were in good agreement with the experimental data. Then, the numerical simulation of the coupled heat transfer problem of a typical ultra-high temperature ceramic (UHTC) material is considered. The influence of the heat transfer effect on the aerodynamic thermal environment and the thermal response of the structure is considered. The results show that for the UHTC with complex shape and relatively high thermal conductivity, The influence of internal heat conduction on the thermal environment and surface temperature distribution of materials and structures can not be neglected. Finally, the influence of thermophysical properties (specific heat and thermal conductivity) of UHTC material on the supersonic flow and heat transfer process is studied. The results show that when the specific heat and thermal conductivity are within a reasonable error range, the surface temperature response Not sensitive to its change.