Continuum damage mechanics based failure prediction and damage assessment in laminated composite structures

Abstract

In the present work, nonlinear mechanical response of laminated composite structures is investigated by a constitutive numerical model based on damage mechanics. A numerical method is included in progressive damage analysis to simulate the damage accumulation and failure response of composite structures under service load conditions. This model is capable of predicting the residual strength and residual stiffness of laminate with arbitrary lay-up and geometry. The state-of-the-art progressive damage model exploits a set of stress-based Hashin-type criteria and a set of appropriate degradation rule of ply discount. The constitutive model is developed wherein the damage initiation criteria are based on Hashin failure criterion for damage evolution. The proposed progressive damage model involves the steps of stress analysis, failure analysis, and material properties degradation. This work involves a comprehensive study of quasi-isotropic elliptical hole specimen to develop the failure model. Overall, the results of the exercise aid in design applications to predict the impact of progressive damage in aircraft composite structures under service loads.