Composite laminates are subjected to five-point bending test conditions, resulting in cracks and delaminations in the laminate. A theoretical model is also developed to represent the five-point bending configuration, resulting in the calculation of the through-the-thickness distribution of stresses and strains. The results of the theoretical analysis and the five-point bending tests are presented. The stress and strain distributions arising from the theoretical model, together with knowledge of the laminate stacking sequence, can be used to predict the type and location of failures under five-point bending test conditions.
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