Skin-stiffener joints possess a critical role in aerospace structures, but there is a lack of advanced numerical failure prediction methods with physically based failure criterion in the literature. LaRC05 failure criterion combined with a progressive failure model and cohesive zone are used to simulate the failure of a carbon fiber reinforced composite T-joint subjected to pull-off loading. The results are validated with experimental tests. The model shows excellent accuracy in failure load prediction and determination of failure locations. Parametric studies indicate its robustness in terms of sensitivity to difficultly obtainable material properties required for the criterion. Compared to other criterion, the LaRC05 criterion captured the location of laminate failure with higher confidence.
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