Panel flutter analysis of general laminated composite plates
Panel flutter analysis of general laminated composite plates
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DOI：
10.1016/j.compstruct.2010.05.001
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发表时间：
2010-11
影响因子：
6.3
通讯作者：
M. A. Kouchakzadeh;M. Rasekh;H. Haddadpour
中科院分区：
文献类型：
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作者：
M. A. Kouchakzadeh;M. Rasekh;H. Haddadpour
研究了一般复合材料层合板在超声速气流中的非线性气动弹性问题。结构模型采用经典板理论沿着分布，并考虑冯-卡门非线性应变，气动模型采用线性活塞理论。利用汉密尔顿原理导出了耦合的偏微分运动方程，并利用Galerkin方法将控制方程在时间上化为一个非线性常微分方程组，然后用直接数值积分法求解。研究了面内力、静压差、纤维取向和气动阻尼对板非线性气动弹性行为的影响。结果表明，纤维取向对板的动力学行为和非对称性有显著影响，改变了板的极限环振荡行为。
The problem of nonlinear aeroelasticity of a general laminated composite plate in supersonic air flow is examined. The classical plate theory along with the von-Karman nonlinear strains is used for structural modeling, and linear piston theory is used for aerodynamic modeling. The coupled partial differential equations of motion are derived by use of Hamilton’s principle and Galerkin’s method is used to reduce the governing equations to a system of nonlinear ordinary differential equations in time, which are then solved by a direct numerical integration method. Effects of in-plane force, static pressure differential, fiber orientation and aerodynamic damping on the nonlinear aeroelastic behavior of the plate are studied. Results show that the fiber orientation has significant effect on dynamic behavior of the plate and the asymmetric properties, changes the behavior of the limit cycle oscillation.