Nonlinear Panel Flutter Analysis of FG Plates with Cutout in Supersonic Flow

In this paper, the nonlinear aeroelastic behavior of functionally graded plates in the presence of square cutouts is studied in supersonic flow. The von-karman large deflection plate theory is used to account for structural nonlinearity and also quasi-steady piston theory is employed to estimate the aerodynamic pressure induced by the supersonic airflow, respectively. A continuous grading approach in the direction of thickness is attributed to the material properties of the plate. The derived nonlinear partial differential equations are transformed into a set of coupled nonlinear ordinary equations using the Galerkin method and then solved by numerical time integration. Results show that the size of the cutout affects the critical dynamic pressure and the nonlinear response of the plate dramatically.