高超声速飞行器流固热多场耦合问题研究

The Analysis of fluid-solid-thermal multi-field coupling is the key technology of hypersonic vehicle development. But there are still several problems need to be solved urgently, such as low accuracy of aerodynamic heating computation, immature coupling methods, the development of flutter test method and lack of the knowledge of wind tunnel test implementation, et al. In view of the above problems, this project carries out the following research work: 1. Develop CFD methods for aerodynamic force and aerodynamic heating simulation with high accuracy; 2. Develop numerical simulation techniques for fluid-solid-thermal multi-field coupling problem with high efficiency; 3. Carry out researches on wind tunnel test of hypersonic aerothermoelastic problems and the consistency between numerical and test results; 4. Reveal the interaction mechanism of fluid-solid-thermal multi-field coupling and investigate the behavioural rules of each internal factors involed in the interaction process; 5. Develop a set of computational software, with independent intellectual property rights and excellent verification and validation, for hypersonic vehicle aerothermoelastic problems. The research achievements of this project could provide theoretical basis and important supporting technologies for hypersonic vehicle development.

高超声速飞行器的流固热多场耦合问题涉及到热/化学反应非平衡流动与辐射特性、激波边界层干扰、非线性气动力/结构变形/结构传热相互耦合作用等复杂物理化学过程，对这些问题进行深入研究，不仅是高超声速飞行器设计和发展的迫切需求，也是对研究人员的极大挑战。本课题以高超声速飞行器流固热耦合问题为研究对象，拟开展以下研究：1）建立气动力与气动热高精度CFD计算方法；2）发展高效流固热多场耦合问题的数值模拟技术；3）开展高超声速气动热弹性的风洞试验以及数值计算和试验结果间的一致性研究；4）揭示流固热多场耦合的物理机理，探索其内部各因素作用规律；5）开发一套具有自主知识产权和验证良好的高超声速飞行器气动热弹性专用计算软件。本项目的研究成果将为高超声速飞行器设计提供理论基础和重要技术支撑。

流固热耦合分析方法是高超声速飞行器研制中的关键技术之一，本项目针对流固热多场耦合中许多亟待解决的问题，如：气动热计算精度低、耦合计算不完善和数值稳定性差、缺少试验模型设计理论与风洞试验方案等问题，开展了系统深入的研究：（1）建立了高精度气动力、气动热CFD计算方法；（2）发展了一种高效气动热弹性耦合分析技术；（3）开发了一套具有自主知识产权的高超声速飞行器多场耦合专用计算软件；（4）发展了高超声速气动弹性的风洞试验理论和方法，并设计制作了吹风试验模型，开展了气动热弹性风洞试验。在气动热高精度计算方法、流固热耦合算法的数值精度和稳定性、气动热弹性风洞模型设计与风洞试验方法等方面均有重要突破，取得大量研究成果，可为高超声速飞行器设计提供理论基础和重要技术支撑。