高超声速气流中复合材料壁板热颤振分析

Flutter Analysis of Composite Panels in Hypersonic Flow with Thermal Effects

针对高超声速气流中的复合材料壁板颤振问题,根据Hamilton原理,利用von Karman大变形应变——位移关系、三阶气动力活塞理论和准定常热应力理论建立了壁板结构颤振的气动弹性力学模型,使用Bogner-Fox-Schmit单元推导出考虑热效应的复合材料板颤振的非线性有限元方程。应用数值积分的方法在时域内求解方程,确定出壁板颤振的临界动压,并分析复合材料壁板的非线性颤振特性。数值模拟的结果表明,在高超声速气流中气动力的非线性项和热载荷对壁板颤振的振动幅值的影响较明显。这将为高超声速飞行器壁板结构的设计奠定基础。

The composite panel flutter in the hypersonic flow is investigated. Based on Hamilton princi- ple, the aeroelastic model of the composite panel is established by using the yon Karman large deflection plate theory, third-order piston theory aerodynamics and the quasi-steady thermal stress theory. In non- linear finite element equations of the motion with the thermal effect, the Bogner-Fox-Schmit element is adopted. The equations are solved in the time domain using a numerical integration method. In virtue of the results, the critical dynamic pressure is determined and the nonlinear flutter characteristics of com- posite panels are analyzed. Numerical results show that the effect of the nonlinear aerodynamic loading and the temperature on oscillations amplitudes of is evident. This will lay the foundation for the design of panel structures in the hypersonic vehicle.