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Fatigue crack growth in airframe materials under a variety of aircraft wing load spectra is numerically analyzed using a simple crack closure based model. An integrated load/damage-exceedance diagram is used to graphically describe the load spectrum as well as crack growth damage distribution. Characteristic features of crack growth damage contribution from individual load cycles are associated with the nature of the load spectrum. The significance of fatigue crack closure and its impact on damage distribution are studied.
fatigue crack, cumulative damage, crack closure, aircraft load spectra
National Aeronautical Laboratory, Bangalore,