航天飞行器壁板结构气动热/气动弹性耦合分析方法研究

项目名称： 航天飞行器壁板结构气动热/气动弹性耦合分析方法研究

项目编号： No.11502024

项目类型： 青年科学基金项目

立项/批准年度： 2016

项目学科： 数理科学和化学

项目作者： 郭静

作者单位： 北京强度环境研究所

项目金额： 20万元

中文摘要： 由于气动加热作用，高超声速飞行器壁板结构经历严酷的高温环境，使其产生很大的热挠度。这将影响其气动特性，甚至改变其颤振边界和颤振特性，极大地影响飞行器的性能甚至飞行安全。本项目针对高超声速飞行器壁板面临的严酷气动热/气动弹性强耦合环境载荷特点，开展气动热对壁板结构颤振特性影响规律、热环境下壁板结构非线性颤振分析方法研究，并通过地面颤振模拟试验进行验证，揭示材料热物性参数改变和热应力共同作用下壁板结构颤振机理，突破气动热/气动弹性双向耦合的壁板非线性颤振分析方法，提升我国在这一领域的研究水平，为热环境下高超声速飞行器结构气动弹性设计提供技术支撑。

中文关键词： 热环境；高超声速；壁板颤振；活塞理论；双向耦合

英文摘要： Because of aerodynamic heating, surface panels of hypersonic vehicles are subjected to rigorous high-temperature environment. Large thermal deflections of the surface panels may occur. This would affect its aerodynamic characteristics, even though flutter boundary and flutter characteristics, leading to poor flight performance and flight safety. Aiming at the feature of extremely aerothermal/aeroelastic strong couple environment for hypersonic panel, studies on the effect of aerothermal loading on flutter characteristics, nonlinear flutter analytical method and ground flutter simulation test method for hypersonic panel under thermal environment are developed. Mechanism of panel flutter under the effects of alteration of material thermal-physical parameters in conjunction with thermal stress is discovered. Moreover, aerothermal-aeroelastic two-way coupling nonlinear flutter analytical method for hypersonic panel is established. Research capability is promoted dramatically in this area. Technical support is provided for design of aero elasticity of hypersonic vehicles structure under thermal environment.

英文关键词： thermal environment;hypersonic;panel flutter;piston theory;two-way coupling