高超声速飞行器流固热多场耦合问题研究

项目名称： 高超声速飞行器流固热多场耦合问题研究

项目编号： No.11472133

项目类型： 面上项目

立项/批准年度： 2015

项目学科： 数理科学和化学

项目作者： 韩景龙

作者单位： 南京航空航天大学

项目金额： 90万元

中文摘要： 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。

中文关键词： 高超音速飞行器；多场耦合；气动生热；热颤振；风洞试验

英文摘要： 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.

英文关键词： hypersonic vehicle;multi-field coupling;aerodynamic heating;thermal flutter;wind tunnel test