Abstract
An exact methodology allowing one to determine the aeroelastic lift distribution and the divergence instability of swept cantilevered composite wing structures is developed in this paper. The approach based on the Laplace transform technique enables one to solve, in a unified manner, both aeroelastic problems. The analysis encompasses the cases of free and constrained warping models for the wing twist. Numerical results are presented to demonstrate the effects played by the fiber orientation, ply lay-up, warping inhibition, and wing geometry on the subcritical static aeroelastic response and on the divergence instability of composite swept wings.
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