Application of progressive fracture analysis for predicting failure envelopes and stress–strain behaviors of composite laminates: a comparison with experimental results

摘要: Abstract The theoretical predictions, published in Part A of the failure exercise, are compared with experimental results provided by organizers exercise. Two computer codes, ICAN and CODSTRAN, developed at NASA (Glenn Research Center Lewis Field), were applied to predict damage initiation, growth global structural fracture a wide range multidirectional laminates. CODSTRAN was employed (I) seven biaxial envelopes [0°] unidirectional [0°/±45°/90°]s, [±30°/90°]s [±55°]s multi-layered composite laminates (II) stress–strain curves for [±55°]s, [0°/90°]s [±45°]s under uniaxial loadings. In general, gave reasonable predictions cases where final dominated fibre fracture. There was, however, large discrepancy between predicted measured strengths strains matrix failure. Some is attributed (a) effect residual stiffness that discounted simulations (b) sensitivity specimens presence stress state certain cases.