Dynamic Instability of Composite Plate under Stress Wave Based on Galerkin Method

Based on the Kirchhoff thin plate theory and Hamilton principle, the vibration control equation of composite plate is established. The equation is simply supported on three sides and fixed on one side with initial geometric imperfections. The expression of buckling critical load is obtained. The numerical calculation is carried out by MATLAB programming. The effects of initial geometric imperfections, initial phase, ply angle, buckling mode order and layer number on the critical buckling load of the plate are discussed. Results show that the critical buckling load is decrease with the increasing of the critical length, the decreasing of the laying thickness, the increasing of the initial geometric defect coefficient, and the decreasing of the initial phase of the mode function. In addition, the smaller the angle between the laying angle of each layer and the load direction is, the greater the buckling critical load is. And the buckling critical load tends to be stable when the layer number of symmetrical laminate reaches seven.