A structural article representative of a large full-production military aircraft wing was subjected to flight-by-flight load spectra to initiate and propagate fatigue cracks in 17 selected fastener holes in eight test areas. One-hundred unit flights were applied to the wing to initiate crack growth at sharp notch sawcuts and existing cracks, followed by 2000 unit flights to propagate the cracks. Seven test areas were monitored for acoustic emission (AE) using a 32-channel AE flaw locator system and triangulated sensor arrays. AE was detected from 12 of the 15 test holes monitored which experienced crack growth. After the tests, the tes holes were removed from the structure fractographic analysis of crack growth.


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    Title :

    Acoustic emission detection of fatigue crack growth in a production-size aircraft wing test article under simulated flight loads


    Additional title:

    Akustischer Nachweis des Ermuedungsrisswachstums in einem Flugzeugtragflaechenteil, der unter simulierter Fluglast geprueft wird


    Contributors:
    Pless, W.M. (author) / Bailey, C.D. (author) / Hamilton, J.M. (author)

    Published in:

    Materials Evaluation ; 36 , 5 ; 41-48


    Publication date :

    1978


    Size :

    8 Seiten, 10 Bilder, 1 Tabelle, 10 Quellen


    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English





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