论文部分内容阅读
The nonlinear combination resonance of a simply supported carbon fiber composite laminated rectangular plate subjected to transversal excitations,in-plane excitation and aerodynamic loads is investigated.Based on the yon Karman-type equations and Reddys third-order shear deformation plate theory,the nonlinear governing partial differential equations of motion for the carbon fiber composite laminated rectangular plate are obtained by Hamiltons principle.