The behavior of short and long fatigue cracks in the widely used damage tolerant aluminum alloy 2024-T3 was compared using flight simulation loading representatives for the Fokker 100 wing/fuselage structure. The results showed that the apparently anomalous behavior of short cracks is not significant for durability analysis of the current wing/fuselage structure. Also the data provide a reference for evaluating new, candidate materials for durable wing/fuselage structures in transport aircraft.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    Short and Long Fatigue Crack Growth in 2024-T3 under Fokker 100 Spectrum Loading


    Contributors:
    R. J. H. Wanhill (author) / L. Schra (author)

    Publication date :

    1990


    Size :

    26 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English





    Modelling of Short Fatigue Crack Growth under Mean Stress Loading

    Wang, C. H. / International Committee on Aeronautical Fatigue | British Library Conference Proceedings | 1995


    Fatigue Crack Growth in D357-T6 and 2024-T3 under Variable Amplitude Loading and Validation of Fatigue Crack Growth Models

    Glancey, C. D. / Stephens, R. / International Committee on Aeronautical Fatigue | British Library Conference Proceedings | 2004


    Quantifying Spectrum Loading Effects on Fatigue Crack Growth

    Zion, H. L. / Johnson, W. S. / Ball, D. L. et al. | British Library Conference Proceedings | 1999