In order to improve the damage tolerance, thickness variations (crenellations) were introduced onto skin and stringers of laser beam welded aluminum alloy 2139-T8 stiffened flat panels. This new panel design was tested under constant amplitude and modified Mini- Twist spectrum to determine the effect of crenellations on the fatigue crack propagation. Additionally, residual strength tests were performed again on center cracked panels. Results were compared with the conventional (constant thickness) welded stiffened panels of the same weight. It was shown that on crenellated panels the stress intensity factor profile for a crack perpendicular to stringers favors substantially lower overall fatigue crack propagation rates (longer fatigue lives) compared to conventional panels. Residual strength tests showed no significant difference between the behaviors of crenellated and conventional panels as expected. This study clearly demonstrates substantial benefit of the crenellations for the improvement of damage tolerance of metallic structures.


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    Title :

    New design philosophy for improvement of damage tolerance of welded airframe structure


    Contributors:
    Uz, M.V. (author) / Kocak, M. (author) / Lemaitre, F. (author) / Ehrström, J.C. (author) / Bron, F. (author) / Kempa, S. (author)


    Publication date :

    2008


    Size :

    10 Seiten, 8 Bilder, 10 Quellen




    Type of media :

    Conference paper


    Type of material :

    Print


    Language :

    English




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