Abstract
ABSTRACTA total fatigue life model proposed previously by the same authors for laminated composite structures subjected to mode‐I fracture loading is evaluated by two newer models. The new models differ from the original model by normalization factor and approximation of stable delamination growth rate equation. All three models include the delamination growth in subcritical (delamination initiation), linear (stable growth) and final (unstable growth) fracture domains. All three models were evaluated by comparing the total life predictions for two different block loadings. One is a normal operation of a rotor craft‐type structure and the other is an aggressive loading. Predicted results of the three models were compared with each other and with the experimental data. The material considered was woven‐roving E‐glass fibre and vinyl ester matrix and the laminate was made by vacuum assisted resin transfer molding.
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