Volume 1, Issue 9 (October 2004)

    Spectrum Fatigue Testing and Small-Crack Life Prediction Analysis on a Coupon Similar to a Critical Design Detail of a CF188 Hornet Component

    (Received 28 May 2002; accepted 17 July 2003)

    Published Online: 2004

    CODEN: JAIOAD

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    Abstract

    Numerous studies have shown that small-crack methodology can be used to predict the total fatigue life of laboratory type (KT = 1 and 3) specimens under variable amplitude loading. Prior to investigating how well this fatigue life prediction capability could be extended to “real” aircraft structures, an intermediary step was taken where total fatigue life was predicted for a laboratory type specimen similar to a critical design detail in a fighter aircraft fuselage bulkhead. Using the small-crack analysis in the computer code called FASTRAN and assuming an initial crack size of 20 microns, the time to catastrophic failure of the test coupons was predicted to within 10% of the average test times.


    Author Information:

    Yanishevsky, M
    Senior Research Officer, Institute for Aerospace Research, National Research Council Canada, Ottawa, ON

    Everett, RA
    Senior Aerospace Engineer, U.S. Army Vehicle Technology Directorate, ARL, Mechanics and Durability Branch, Hampton,


    Stock #: JAI19032

    ISSN: 1546-962X

    DOI: 10.1520/JAI19032

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    Author
    Title Spectrum Fatigue Testing and Small-Crack Life Prediction Analysis on a Coupon Similar to a Critical Design Detail of a CF188 Hornet Component
    Symposium Fatigue Testing and Analysis Under Variable Amplitude Loading Conditions, 2002-05-31
    Committee E08