Fatigue tests have been carried out on aluminum alloy lugs with different hole diameters (d = 10 mm and d = 30 mm) and configurations (Kt = 3.2 and kT = 3.7). A strong improvement in fatigue properties was observed in cases of relative interference fits larger than 0.2 %. The effect of the stresses produced by the interference fit were theoretically analyzed and the critical stress level, below which the interference fit has a beneficial effect, was determined. A method for evaluation of the fatigue life of interference-fit aluminum lugs is proposed. (Biller)


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    Title :

    Fatigue properties of aircraft lugs with interference fit


    Additional title:

    Ermuedungsverhalten von Oesen mit Festsitz an Flugzeugen


    Contributors:
    Buch, A. (author)


    Publication date :

    1976


    Size :

    33 Seiten, 17 Bilder, 5 Tabellen, 20 Quellen


    Type of media :

    Conference paper


    Type of material :

    Print


    Language :

    English




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