Abstract
The present study investigated the effect of damage on the free vibration and the aeroelastic response of variable stiffness (VS) composite laminated plates. The ineluctable defects or internal flaws are incorporated into the finite-element coding through anisotropic damage formulation and coupled with MSC.Nastran using Direct Matrix ion Program to generate the aerodynamic forces at discrete values of reduced frequencies for performing aeroelastic analysis. The sensitive location of damage for the free vibration and flutter characteristics is identified. Thereafter, the best placement of piezoelectric patches is determined to enhance the aeroelastic boundary of the damaged VS plates with active feedback control.
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