Abstract
On the basis of the experimental observation that crack growth in fiber-reinforced-metal laminates (FRMLs) under fatigue loading tends to reach a steady state, a material constant, the equivalent crack length ( l 0) of FRMLs, is proposed. The stress intensity factor equation for FRMLs during fatigue is derived, and a phenomenological model for predicting crack growth in FRMLs developed. Very good agreement was achieved between the predicted fatigue lives from the phenomenological model and the test results. The present phenomenological model can be applied to both center-cracked-tension (CCT) and single-edge-notched-tension (SENT) specimens, requires no knowledge of the bridging traction and the delamination growth in FRMLs, and thus will greatly facilitate engineering application.
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