The fatigue crack growth behavior in the notched fiber metal laminates underconstant-amplitude fatigue loading was analyzed numerically and experimentally. A3-D finite element method (FEM) was established to calculate the remote stressintensity factors and to determine the matrix damage patterns in the fiber/epoxy layers.A 2-D bridging stress approach was established to calculate the bridging stressintensity factors. The fatigue crack growth rates were then calculated using a Paristypeempirical equation of the constituent metal. The predicted crack growth ratescorrelate well with the experimental results.
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