Nonlinear deflection characteristics of damaged composite structure theoretical prediction and experimental verification

Abstract

This research derived a nonlinear computational model for the prediction of deflection responses of the damaged layered composite structures. The model validity was verified using in-house experimentation. The composite panel model has been derived mathematically using the higher-order polynomial kinematics without non-zero shear stress conditions and Green’s strain for the geometrical nonlinearity. The nonlinear deflection responses of combined damage curved shell structures are evaluated numerically utilizing the nonlinear isoparametric finite element technique in conjunction with the direct iterative method. By setting the necessary convergence criteria, the model accuracy has been explored by comparing the deflections of the published literature (the maximum deviation observed is 6.97%). Additionally, the experimentation is done on damaged laminated shell structures, and results are compared to show the proposed model’s efficacy (maximum deviation observed is 2.17%). Finally, a number of numerical examples are solved to assess the effects of the material, geometry and damage-related parameters on the nonlinear deflections of the shell structure.