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Abstract
Progressive failure analysis (PFA) is widely used to predict the failure behavior of composite materials. As a structure becomes more complex with discontinuities, prediction of failure becomes more difficult and mesh dependence must be taken into account. In this study, a PFA model was developed using the Hashin failure criterion and crack band model. The failure initiation was evaluated using the Hashin failure criterion. If failure initiation occurred, the damage variables at each failure mode (fiber tension and compression; matrix tension and compression) were calculated according to linear softening degradation and they were then used to derive the damaged stiffness matrix. This matrix reflected a degraded material, and PFA was continued until the damage variables became “1,” implying complete material failure. A series of processes were performed using the finite element method program ABAQUS with a user-defined material subroutine. To evaluate the proposed PFA model, experimental results of open-hole composite laminate tests were compared with the obtained numerical results. The strain behaviors were compared using a digital image correlation system. The obtained numerical results were in good agreement with the experimental ones.
Highlights
Several studies are being conducted on composite materials to design structures in engineering.In addition to aeronautical fields that have been investigated extensively, studies are being performed in a variety of fields such as the automobile and naval manufacturing industries
The stiffness values were accurately predicted in the range of 3.47% for the tensile test condition and 3.15% for compressive test condition. These results show that the developed Progressive failure analysis (PFA) model can predict the strength and stiffness of the composite laminate accurately regardless of the stacking sequence, load direction condition, and notch effect
Using the Hashin criteria, failure initiation was detected at various failure modes
Summary
Several studies are being conducted on composite materials to design structures in engineering. Stress and failure analysis studies were conducted, and it was confirmed that the suggested PFA model demonstrated a good correlation with the experimental results. This model used the damage variables while taking into consideration the reduction in area induced during the failure. The suggested model demonstrated good mesh independency and predicted the failure behavior of the notched composite laminate. The less mesh dependency of the crack-band-model-applied PFA model can be used to predict the failure behavior of complex composite structures. Results, the efficiency of the suggested model was verified This model effectively predicted the failure behavior of the composite laminate regardless of the stacking sequences. The failure behavior of the open-hole composite laminate specimen was investigated
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