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Supersonic flutter of laminated composite panel in coupled multi-fields

机译：多层复合板在多场耦合中的超音速颤动

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The flutter of a laminate composite panel subjected to aerodynamic, thermal, and acoustic load is investigated in the present study. The von-Karman large deflection plate theory is adopted to account for the geometrical nonlinearities. The third order piston theory is employed to estimate the aerodynamic pressure induced by the supersonic airflow. The acoustic excitation is considered to be a stationary white-Gaussian random pressure with zero mean, and the temperature field is assumed to be a constant in the modeling process. Based on the Hamilton principle, the coupled partial differential governing equations of the panel are established and then the assumption mode method is adopted to truncate the governing equations to a set of nonlinear ordinary differential equations, which are then solved by the fourth-order Runge-Kutta numerical integration method. The simulation shows that both the acoustic and thermal loadings have significant effect on the dynamic response of the panel at high acoustic pressure level. (C) 2015 Elsevier Masson SAS. All rights reserved.
机译：在本研究中，研究了层压复合板在空气动力，热和声载荷作用下的颤动。采用冯-卡尔曼大挠度板理论来解决几何非线性问题。采用三阶活塞理论来估算超音速气流引起的空气动力压力。声激励被认为是均值为零的平稳白高斯随机压力，并且在建模过程中假定温度场为常数。基于汉密尔顿原理，建立面板的耦合偏微分控制方程，然后采用假设模式方法将控制方程截断为一组非线性常微分方程，然后由四阶Runge-求解。 Kutta数值积分法。仿真表明，在高声压水平下，声载荷和热载荷都对面板的动态响应产生重大影响。 （C）2015 Elsevier Masson SAS。版权所有。

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