Abstract
ABSTRACT This study presents the finite element (FE) solutions to the aeroelastic flutter behaviour of multi-layered composite shell panels with flat and cylindrical geometry under supersonic flow based on third-order shear deformation mid-plane kinematics. The shell panel is discretized by a nine-noded isoparametric shell element with nine nodal degrees of freedom. The effect of the aerodynamic load is incorporated through first-order piston theory. The numerical model's accuracy and validity are justified by comparing the present solutions (free vibration frequency, coalescence frequency, and the corresponding critical aerodynamic pressure) with the existing numerical results. Also, the current natural frequencies are compared with the values from in-house experimental tests. The influence of parameters such as the flow angle, fibre orientation, material anisotropy, thickness ratio, and curvature ratio on the supersonic flutter boundaries of the shell panels subjected to simply supported and clamped conditions is investigated. The results are deliberated in detail, and it is observed that the fibre orientation and material anisotropy affect the flutter boundary differently under the simply supported and clamped conditions. Moreover, the first coalescence is greatly influenced by the flow angle instead of the curvature of the curved shell panels.
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