13th International Conference on Fracture June 16–21, 2013, Beijing, China -4- Fig 4 Bridging stresses distributions in t Fig 5 Comparison for as is 20mm Fig 6 Comparison for as is 10 mm Fig 7 Comparison for as is 5mm Table 1 The comparisons between experimental and predicted fatigue lives of FMLs 2as (mm) Experiments （N） Predictions （N） Errors（%） 5 1024000 1067019 4.2 10 355600 363672 2.3 20 296000 277720 6.2 Actually, the accuracy of this numerical approach depends on the delamination shape and the ratio . The delamination shape can be ellipse, parabola, triangle and cosine. Through the calculation, triangle seems to be the best delamination shape, cosine to be the second, parabola and triangle don'tfit well with the experimental results. The predictions are also sensitive to the radio .But a range of the radio can be determined by experimental observations so that the errors can be controlled. This paper proposes a modified numerical approach for predicting the fatigue crack growth rates in different notched FMLs. By using MATLAB, the fatigue crack growth rates and the fatigue lives of different notched FMLs are calculated, and good agreement is achieved between the predictions and experimental results. References [1] Roebroeks G.H.J. Towards GLARE - The development of a fatigue insensitive and damage tolerant aircraft material [D]. PhD Thesis, Delft University of Technology, Delft, 1991. [2] Alderliesten R.C. Fatigue crack propagation and delamination growth in GLARE[D]. PhD Thesis, Delft University of Technology, Delft, 2005.
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