Geometrical Nonlinear Analysis of Composite Laminated Plates with Three Edges Clamped and One Edge Simply Supported Using High-Order Shear Deformation Theory
Yang Jiaming(1,2), Sun Liangxin(1)
(1 Nanjing University of Aeronautics and Astronautics, Nanjing, 210016) 
(2 Nanchang Institute of Aeronautical Technology, Nanchang, 330034)

Abstract: Geometrical nonlinear governing equations and their boundary conditions of composite laminated plates are obtained in the form of displacements by t he virtual displacement principle. The study is based on the Reddy's high-order shear deformation theory. All five-displacement functions satisfy the boundary conditions that three edges are clamped and one edge is simply supported. Galerkin's method is used to transfer non-dimension alized governing equations to anfinite set of nonlinear algebraic equations. Large scale of sparse matrix linear equations has been solved by Biconjugate Gradients Stabilized Method and nonlinear algebraic equations solved by parameter regulated iterative procedures. Numerical results are presented in a dimensionless graphical form that relates to the performances of symmetric cross-ply laminated plates subjected to the uniformly distributed loads. The influence of various factors on deflection and moment is studied.
Keywords: Three edges clamped and one edge simply supported, composite laminated plates, high-order shear deformation theory, geometrically nonlinear.