Corrosion-fatigue is one of the damage mechanisms affecting the structural integrity of the aging aircraft. Simple analytical and probabilistic models for predicting pitting corrosion and corrosion-fatigue life in aluminum alloy 2024/T3 used in aircraft structures is presented. The developed model includes the effect of the interaction of cyclic load and the corrosive environment on the fatigue life, and considers all stages of the corrosion-fatigue process. The probabilistic model investigated considers the uncertainties in initial pit size, corrosion pitting current, and material properties due to scatter found in the experimental data. The analytical model shows very good quantitative agreement with the existing experimental data and analytical models over a wide range of parameters. The results predicted that the crack initiation life varies approximately 10 % - 40 % as compared to crack propagation life in corrosion-fatigue problems.


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    Title :

    Comparative study of corrosion-fatigue in aircraft materials


    Additional title:

    Eine vergleichende Studie zum Korrosions-Ermüdungsverhalten von Flugzeugwerkstoffen


    Contributors:

    Published in:

    AIAA Journal ; 39 , 2 ; 325-330


    Publication date :

    2001


    Size :

    6 Seiten, 6 Bilder, 3 Tabellen, 14 Quellen




    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English





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