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Fatigue crack growth (FCG) experiments were conducted on controlled variations of Type 7075 and 7050 aluminum alloys. Alloy FCG resistance was ranked under constant amplitude and simple variable amplitude load spectra. Fracture mechanics and fractographic approaches were used to interpret causes for variation in ranking of 7XXX aluminum alloy FCG resistance with loading conditions. The interpretation is built around clarification of a controlling FCG mechanism that is dependent upon interaction of microstructure and load history. This clarification represents a necessary first step toward knowing which microstructure or which design (test) procedure is optimum for a particular class of application, for example, fighter as opposed to bomber or transport aircraft.
aluminum alloys, fatigue (materials), crack growth, aircraft, material selection, test methods, spectrum loading, fracture mechanics, fractography, microstructures, crack propagation
Staff engineer, Engineering Properties and Design Division, Alcoa Laboratories, Alcoa Center, Pa.
Pratt and Whitney, Aircraft Division, West Palm Beach, Fla.
Fatigue and Fracture Research Laboratory, Georgia Institute of Technology, Atlanta, Ga.
Alcoa Davenport Works, Davenport, Iowa
Alloy Technology Division, Alcoa Laboratories, Alcoa Center, Pa.