高超声速气流中受热壁板的非线性气动弹性声振特性分析

Due to the severe service environment of panel structure of hypersonic flight vehicle, the conventional panel flutter evolves as the aeroelastic vibroacoustic problem of heated panel subject to the coulping of multi-physics including fluid, solid, thermo and acoustic fields. In this project, with the modelling of nonlinear aeroelastic vibroacoustic system of heated panel, the analysis nonlinear aeroelastic vibroacoustic characteristics of heated panel together with parametric studies, analysis of the influence of aeroelastic effect on the vibroacoustic characteristics of heated panel will be performed. The aim of this projet is to illuminate the mechanism of complex dynamics phenomenon of panel structure subject to the coupling of fluid-thermo-acoustic fields, and to clarify the stability mechanism of panel aeroelastic vibroacoustic system subject to mutli physics. As the result, the framework for the prediction of nonlinear aeroelastic vibroacoustic response will be established. The effects of acoustic and thermo fields on the subcritical and supercritical beheaviours of panel aeroelastic vibroacoustic stability will be made clear. The project will provide nonlinear aeroelastic vibroacoustic analysis model and prediction method for the dynamic strength design of airframe panel of hypersonic vehicles. The research on this project will also find new complex dynamic phenomenon for the panel structure in hypersonic airflow field, and promote the studies on dynamic stability subject to multi-physics.

高超声速飞行器机体壁板严酷的声热服役环境，使得壁板颤振这种传统的气动弹性力学问题演变为流-固-热-声多物理场耦合下的受热壁板气动弹性声振问题。通过对受热壁板的非线性气动弹性声振系统建模，受热壁板非线性气动弹性声振特性分析和参数影响分析以及气动弹性效应对受热壁板声振特性的影响规律分析，阐明声场-流场-温度场耦合作用下壁板结构产生复杂动力学现象的力学机理，以及多物理场耦合下壁板气动弹性声振稳定性问题的产生机制，构建高超声速气流中受热壁板的非线性气动弹性声振响应预测分析框架，弄清噪声场和温度场对壁板在其气动弹性声振稳定性亚临界和超临界区域的力学行为的影响规律，为高超声速飞行器机体壁板结构的动强度设计提供非线性气动弹性声振分析模型和分析方法。对发现高超声速流场中壁板结构更加复杂的动力学现象，为多场耦合下的动力学稳定性研究拓展出新的研究方向，起到一定的促进作用。

超/高超音速飞行器壁板结构在气动力、气动热环境及附面层/发动机带来的噪声激励的综合作用下容易产生热声疲劳损伤，影响结构的使用寿命。为了分析流场-温度场-噪声场耦合作用下壁板的非线性气动弹性声振响应特性，本项目开展了以下研究：受热壁板的非线性气动弹性声振系统建模，受热壁板非线性气动弹性声振特性分析和参数影响分析，气动弹性效应对受热壁板声振特性的影响规律分析，基于能量法的壁板气动弹性特性分析和基于能量有限元的受热壁板高频气动弹性声振响应分析。通过本项目的研究，建立了热载荷、噪声载荷、气动载荷共同作用下壁板的非线性声热气动弹性模型，发展了高超声速气流中壁板的非线性气动热弹性声振响应预测方法，研究了流场、温度场和噪声场参数对壁板气动弹性声振响应的影响，以及噪声载荷作用下受热壁板非线性气动弹性声振系统在亚临界稳定区域、临界稳定状态和超临界稳定区域的力学行为，分析了噪声场-流场-温度场耦合作用下壁板产生复杂动力学现象的机理，揭示了气动弹性效应对受热壁板声振响应特性的影响规律。本项目的研究为高超声速飞行器壁板结构的声、热、流、固多物理场的耦合建模和分析，高超声速飞行器壁板结构的动态响应预计及抗噪声疲劳设计，提供了理论和方法基础，具有现实的科学意义和工程应用前景。