Due to their specific mechanical properties composite materials have become an interesting alternative to metallic materials. Moreover, the use of well chosen lay-up allows to get mechanical properties convenient with the structure sollicitations. Finally, they are considered insensitive to fatigue. For these reasons, during the last years, the use of composite materials in aeronautical, shipbuilding or train industries significantly increased. In this study, we propose a modelisation of matrix cracking in composite materials subjected to quasi-static or cyclic loading. In a first time, the experimental analysis allows us to capitalize information to identify characteristics and parameters to be considered in modelling. Based on these results, we propose a modelling of matrix-cracking. We propose an fatigue damage evolution law that we implemented in the finite element code called ZeBuLoN. After identifying different model parameters from experimental results we propose an application of the model in the case of a structure to validate our model. For this, we developed a computational strategy based on the skip cycles method. Finally, we applied our model to the case of a perforated plate structure.
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