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首页> 外文期刊>Composite Structures >Nonlinear aeroelastic flutter and dynamic response of composite laminated cylindrical shell in supersonic air flow
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Nonlinear aeroelastic flutter and dynamic response of composite laminated cylindrical shell in supersonic air flow

机译：超声速气流中复合材料叠层圆柱壳的非线性气动弹性颤振和动力响应

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摘要

Aeroelastic flutter characteristics and dynamic response of a composite laminated circular cylindrical shell under combined action of radial harmonic excitation, compressive in-plane force and aerodynamic pressure are studied in this paper. The first-order piston theory is employed to model the aerodynamics pressure. Partial differential equations governing the vibrations of the cylindrical shell are derived based on the Hamilton's principle and the Donnell's nonlinear shell theory. The Galerkin's method is adopted to discretize the partial differential governing equations to a set of nonlinear ordinary differential equations. The four-dimensional averaged equation is obtained by applying the method of multiple scales under the case of 1:2 internal resonance. The critical free stream static pressure originating flutter of the shell is determined by solving the eigenvalue problem. The phase portrait and time history diagrams are presented to demonstrate the character of the limit cycle oscillation of the shell. The influence of different geometrical parameters, such as the radius, length and thickness of the shell, on the flutter characteristics of the composite laminated circular cylindrical shell are discussed in details. The influences of the amplitudes of the in-plane and transverse excitations on the frequency response curves and force-response curves are also investigated. (C) 2017 Elsevier Ltd. All rights reserved.
机译：研究了在径向谐波激励，面内压缩力和空气动力压力共同作用下的复合材料叠层圆柱壳的气动弹性颤振特性和动力响应。一阶活塞理论用于模拟空气动力学压力。基于汉密尔顿原理和唐内尔非线性壳理论，推导了控制圆柱壳振动的偏微分方程。采用Galerkin方法将偏微分控制方程离散为一组非线性常微分方程。通过在内部共振为1：2的情况下应用多尺度方法获得四维平均方程。通过解决特征值问题来确定由壳体引起的自由流临界静压的临界值。给出了相图和时程图，以说明壳的极限循环振荡的特性。详细讨论了壳的半径，长度和厚度等不同几何参数对复合叠层圆柱壳颤振特性的影响。还研究了面内激励和横向激励的幅度对频率响应曲线和力响应曲线的影响。 （C）2017 Elsevier Ltd.保留所有权利。

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