نوع مقاله : مقاله پژوهشی
1 کارشناس ارشد سازه های هوایی / دانشکده مهندسی هوافضا، دانشگاه صنعتی شریف
2 عضو هیات علمی / دانشکده مهندسی هوافضا، دانشگاه صنعتی شریف
عنوان مقاله [English]
Nonlinear vibration analysis of cross-ply laminated composite shallow circular cylindrical shell was performed. This study applies the Hamilton's principle and Galerkin's method to establish the governing equations of motion and obtain the spatial mode shapes. The geometric non-linear strains are of the von Karman type, boundary condition is clamped-clamped and the shell is subjected to radial dynamic excitation. The modal expansion, considered as a summation of modes, is directly substituted into the non-linear equation of motion for the shell based on the von Karman non-linear strain, and the Galerkin’s method is applied to obtain the governing non-linear equations of motion in generalized coordinates. The resulting ordinary differential equations are solved by the Runge-Kutta method. Using the presented model, the effects of lamination sequence and material properties on the vibration characteristics of the shell are studied and some conclusions are drawn. The results are compared with previous studies and finite element analysis.