高超声速流中壁板的热弹性气动颤振及其主动控制

项目名称： 高超声速流中壁板的热弹性气动颤振及其主动控制

项目编号： No.91216106

项目类型： 重大研究计划

立项/批准年度： 2013

项目学科： 数理科学和化学

项目作者： 曹登庆

作者单位： 哈尔滨工业大学

项目金额： 82万元

中文摘要： 针对高超声速飞行器的飞行马赫数高，气动加热效应大的特点，研究高超声速流中的壁板在弹性力、惯性力、气动力、热应力和声载荷耦合作用下的非线性动态响应与热颤振及其抑制问题。首先建立温度与飞行速度和飞行环境变量的依赖关系，并将热应变和平面初应变计入系统的本构方程；基于von-Kaman大变形非线性几何理论，采用虚功原理建立壁板的非线性动力学模型，作用在壁板上的气动力采用三阶活塞理论模拟，高超声速气流中的随机声载荷则采用零均值高斯随机函数模拟。通过数值积分和模拟试验，分别从理论、数值和试验多方面多层次研究壁板在多场耦合作用下的动力学响应，揭示颤振产生的机理。最后，采用在壁板中加入压电薄膜和压电片的方式，利用压电材料的特性实现壁板颤振的主动控制，为近空间飞行器的动力学与飞行控制设计提供依据。

中文关键词： 高超声速飞行器；多场耦合；热弹性颤振；振动控制；非线性动力学

英文摘要： Keeping in mind the special characteristics of high Mach number and significant effect of thermodynamics for the hypersonic vehicles, this project focused on the investigation of the nonlinear dynamical responses, the thermoelastic flutter and its suppression of the panel in a hypersonic flow under the coupling actions of elastic and inertia forces, aerodynamics, thermal stress, and the sound loadings. First of all, the temperature is determined in terms of the flight speed and the environment variables, and the heat strain and the initial plan strain are countered in the constitutive equations, the nonlinear dynamical equations of the panel are established based on the von-Kaman large deformation nonlinear geometrical theory using the principle of virtual work. The third order piston theory is adopted to describe the aerodynamics, and the Gaussian random functions with zero-mean is employed to describe the stochastic sound loadings acted on the panel in a hypersonic flow. Through numerical integrations and model tests, the dynamical responses of the panel in the coupled actions of multi-physical fields are studied using theoretical, numerical, and experiment approach, respectively. In this way, the mechanism of the onset of the flutter is revealed. Finally, embedding piezoelectric films and pieces into the pane

英文关键词： Hypersonic aircraft；multi-fields coupling；thermo-elastic flutter；vibration control；nonlinear dynamics