Nonlinear Flexural Analysis of Shallow Carbon/Epoxy Laminated Composite Curved Panels: Experimental and Numerical Investigation

In this work, the nonlinear flexural behavior of laminated carbon/epoxy composite panels is investigated numerically using a generalized nonlinear mathematical model based on two higher-order shear deformation midplane kinematics and Green-Lagrange type geometrical nonlinearity. The exact flexural behavior of the laminated panel is computed by considering all the nonlinear higher order terms in the present mathematical model. The nonlinear governing equations are obtained using variational principles and discretized through suitable finite-element steps. The desired nonlinear responses are computed numerically using the direct iterative method. The proposed nonlinear models have been validated by comparing the responses with those available in published literature and the experiment (three-point bend test) as well. In addition, the linear and nonlinear flexural responses of the laminated carbon/epoxy flat panel are also computed using ANSYS 13.0 simulation finite element analysis package. Finally, the efficacy and applicability of the proposed models have been checked by solving some numerical examples for different geometrical parameters (thickness ratio, aspect ratio, curvature ratio, and constraint condition) and discussed in detail. The practical importance of the proposed nonlinear higher-order theory for the laminated structure is highlighted by comparing the linear and nonlinear responses with experimental (three-point bend test) and simulation results.