Abstract
The influence of cyclic bending moment on the delamination and the fatigue crack propagation behavior in Al/GFRP laminate such as the wing section was investigated. The main objective ofbr/ this study was to evaluate the relationship between crack profile and delamination behavior. And a propose parameter on the delamination growth rate(dA_D/da) of Al/GFRP laminates with a saw-cut using relationship between delamination area(A_D) and cycles(N). crack length(a). stress intensity factor range(??K). Also. the fiber bridging effect factor(F_BE) was propose that the fiber bridging modification factor( ?? _fb) to evaluate using the delamination growth rate(dA_D/da). The shape and size of the delamination zone formed along the fatigue crack between aluminum alloy sheet. Glass fiber-adhesive layer were measured by an ultrasonic C-scan image. The shape of delamination zone turns out to be semi-elliptic with the contour decreased non-linearly toward the crack tip. It represents that relationship between crack length and delamination growth rate(dA_D/da) were interdependent by reciprocal action, therefore it's applicable present a model for the delamination growth rate(dA_D)/da) in Al/GFRP laminates.
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