Abstract
AbstractThis paper deals with the investigations of supersonic flutter characteristics of laminated composite plates. The composite plates are modelled using a recently developed nonpolynomial shear deformation theory, which considers the required shear deformation effects in terms of an inverse hyperbolic function of thickness coordinate. The aerodynamic load is calculated by implementing linear piston theory including the influence of yaw angle. An isoparametric generalized finite-element formulation is developed for the aeroelastic analysis taking into account of required structural equations such as constitutive relations, kinematics relations, displacement field, and the principle of minimum potential energy together with the supersonic aerodynamics based on linear piston theory. The results are obtained by solving the developed system of governing equations for the flutter boundary, and the obtained results are validated against the existing analytical and numerical solutions. It is concluded that t...
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