Abstract
A simple theoretical model based upon the equivalent constraint model 1,2 and a sublaminate approach 3 is used to determine the strain energy release rate, G ed, in [± ϑ m 90 n ] s carbon/epoxy laminates loaded in tension. The analysis provides closed-form expressions for the reduced stiffness due to edge delamination and matrix cracking and the total strain energy release rate. The parameters controlling the behaviour are identified. The effect of laminate stacking sequence, matrix crack density and hygrothermal stresses on G ed is examined. Results show that the available energy for edge delamination is increased notably due to transverse ply cracking. Also, residual thermal stresses increase substantially the strain energy release rate and this effect is magnified by the presence of matrix cracking. Finally, predictions for the edge delamination onset strain are in acceptable agreement with experimental measurements.
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