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- W2335192021 abstract "The relationship between crack growth rate under variable amplitude spectrum and the stress intensity per unit stress W is found to be unique for similar loading spectra. Once this relationship, (a), is established, the cycle-by-cycle integration is not needed and simple integration of f ( O r ) ! ' can be applied to obtain the crack growth curve. An illustration of the da/dF YS. c1 approach as recommended for the A-10A Damage Tolerance Reassessment is demonstrated. It includcstwo different stress spectra applied on coupon tests with various geometry and loading configurations. The function f (a) assumes the form used by the Forman equation for da/dN, normalized about some reference stress. This function is shown to fit best the data points gcnerated by the coupon test." @default.
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- W2335192021 date "1980-01-14" @default.
- W2335192021 modified "2023-09-27" @default.
- W2335192021 title "Practical method of fatigue crack growth analysis for damage tolerance assessment of aluminum structure in fighter type aircraft" @default.
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- W2335192021 doi "https://doi.org/10.2514/6.1980-405" @default.
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