Optimization of Free Vibration and Flutter Analysis of Composite Plates Using a Coupled Method of Genetic Algorithm and Generalized Differential Quadrature

Abstract

In this study, the optimization of free vibration and flutter analysis of a composite plate with the implementation of different boundary conditions is investigated. The governing equations of a composite plate are obtained using the first shear deformation theory (FSDT) of plates. The first-order piston theory is utilized to simulate aerodynamic loads, including arbitrary yaw angle over the panel area. The coupled method of genetic algorithm with well-known generalized differential quadrature (GDQ) method is then developed to obtain optimal layup, which led to maximum fundamental frequency and optimized critical flutter aerodynamic pressure. To achieve this aim, the free vibration and flutter analysis of a composite plate will be conducted via the obtained eigenvalue problem by establishing the discretized governing equations and applying boundary conditions. The obtained results are compared and validated with the available results in the literature, which show high accuracy and a fast rate of convergence. Also, the influence of changing in the yaw angle, number of layers, thickness-to-length ratio, boundary conditions and turning symmetric layup to asymmetric layup is studied.