Abstract
A finite element formulation is presented for the effects of arbitrary flow direction on the large amplitude supersonic flutter of composite panels. The von-Karman large-deflection plate theory is used to account for large amplitude limit-cycle oscillations, the quasi-steady first-order piston theory aerodynamics is employed for aerodynamic loading, and the first-order shear deformation theory is used for laminated composite panels. An efficient solution procedure is presented by using the modal transformation to reduce the number of nonlinear panel flutter equations and then applying the linearized updated-mode with nonlinear time function approximation lo the reduced nonlinear panel flutter modal equations. A modal participation is ~defined and the minimum number of linear modes for accurate and converged limit-cycle response can be assured. Examples are given for isotropic and composite panels at yawed supersonic
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