中文摘要：

通过分析高超声速流场-热-结构耦合问题的机理过程,对多场耦合模型进行了数学物理描述,以此发展了松耦合分析策略框架。在此基础上,采用自适应耦合计算时间步长、混合插值策略和复杂外形网格变形等方法,实现了多场耦合分析平台。针对高超声速飞行器进气道前缘结构的耦合特征进行了初步分析研究,计算结果揭示了在持续长时间飞行条件下流场-热-结构耦合的时空分布特征,为深入开展高超声速飞行器热防护系统的综合性能评估及优化提供了理论与技术支撑。

英文摘要：

By analyzing the mechanism of hypersonic fluid-thermal-structural coupling problem, a multi-field coupling model was described mathematically and physically, and a loose coupling analysis strategy framework was developed. On the basis of this framework, a multi- field coupling analysis platform was realized by using adaptive coupling step-size, hybrid interpolation strategy, and mesh deformation method for complex configuration. A preliminary analysis was conducted on the coupling characteristics of the leading edge of hypersonic vehicle inlets. The calculated results reveal the temporal-spatial characteristics of the fluid-thermal- structural coupling problem in long-time aeroheating environments, and provide theoretical and technical support for the comprehensive performance evaluation and optimization of the thermal protection system of hypersonic vehicles.