Analysis and optimal design for supersonic composite laminated plate

The present paper is concerned with the vibration of supersonic laminated plates with general edge conditions. The critical aerodynamic pressure for different types of laminated plate is studied by considering the thermal effects. It is found from the numerical results that, with the increase of aerodynamic pressure for different edge conditions of supersonic plates, the first critical flutter modes are different and in some cases with the increase of aerodynamic pressure the buckling occurs before the flutter. Using a layerwise optimization approach (LOA), the optimal fiber orientation angles of supersonic laminated plate are determined to obtain the maximum critical aerodynamic pressure. It clearly demonstrated that through the optimization process, one can largely raise the critical aerodynamic pressure and significantly improve the stability of supersonic plates.