中文摘要：

新一代高超声速飞行器的发展给防热设计问题带来严峻挑战。根据飞行器热环境多场耦合特性，提出了一种基于多场耦合的热环境数值分析策略，并在此基础上发展了基于 Navier-Stokes 方程的流场 CFD 分析程序，通过有效的界面数据传递算法，实现了与结构有限元热分析软件的耦合，形成了基于流场与结构耦合传热的飞行器热环境多场耦合数值分析方法。以典型圆管前缘为计算模型进行了程序验证，并对稳态和非稳态飞行环境下的流场与结构耦合传热特征和规律进行了数值分析研究。结果分析表明，该方法能够有效地刻画流场与结构之间的耦合传热特征和规律，预测和分析飞行器热环境的空间和时间分布特性，从而可为防热设计的选材和优化提供可靠的参考依据和分析手段。

英文摘要：

The development of new-generation hypersonic vehicles presents a major challenge in the de-sign of thermal protection systems.Sustained hypersonic flight within the atmosphere can result in severe aerodynamic heating phenomena.It is a physical fact that significant interaction occurs between the external aerodynamic heating and the structural heat transfer within the vehicles.Through analyzing the multi-field coupling characteristics of aerothermal environment of hypersonic vehicles,a multi-field coupling numerical analysis approach for predicting aerothermal environment is proposed in this paper.This approach couples the computational fluid dynamics （CFD）codes based on the Navier-Stokes equations with the general com-mercial finite element method （FEM）software by the reliable interfacial data exchange method.Considering a cylindrical leading edge as test case,the fluid-structural thermal coupling characteristics along the steady and unsteady flight trajectory is numerically investigated.It is indicated that the proposed approach could ac-curately predict the fluid-structural thermal coupling characteristics,and achieve the analysis of spatial and temporal distribution characteristics of aerothermal environment,thus providing the reliable analysis tool for the material selection and optimization in the design of thermal protection systems.