Active flutter suppression of damaged variable stiffness laminated composite rectangular plate with piezoelectric patches

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 Abstraction 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.

Automated summary

In this study, the effect of damage on the free vibration and aeroelastic response of variable stiffness composite laminated plates was investigated. Anisotropic damage formulation was used to incorporate ineluctable defects into the finite-element coding, and MSC.Nastran coupled with Direct Matrix Abstraction Program was used to generate aerodynamic forces for aeroelastic analysis. The sensitive location of damage was identified, and the optimal placement of piezoelectric patches was determined to enhance the aeroelastic performance of damaged VS plates with active feedback control.