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    Fatigue Crack Growth in Aircraft Main Landing Gear Wheels

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    Fracture analysis of aircraft landing gear wheels under service-simulated operating loads using various fatigue crack growth characterization techniques is presented. Baseline constants for the wheel forging alloy 2014-T6 aluminum are established. The stress-intensity factors for a two-dimensional surface crack are developed using a proposed load model for the wheel's flange/bead seat radius. Crack growth predictions are performed using a modified crack growth (CRKGRO) program under spectrum load blocks. New stress-intensity factor subroutines for combined loads are added to the program library. The analytic results are compared with measured crack growth data during full-scale structural tests. Good agreement between analytic and structural test results was obtained, and a damage characteristic curve for the wheel flange is proposed. Qualitatively, fracture surface observations supported proposed crack-tip load models, state of stress, and crack growth data.


    main landing gear wheel, surface crack, 2014-T6 aluminum forging alloy, stress-intensity factor, structural test, crack growth analysis, fractography, baseline constants, fracture mechanics

    Author Information:

    Nagar, A
    Aerospace engineer, Fatigue, Fracture, and Reliability Group, Structural Integrity Branch, AFWAL Flight Dynamics Laboratory, Wright-Patterson Air Force Base, OH

    Committee/Subcommittee: E08.06

    DOI: 10.1520/STP33110S