Analytical and experimental results of the test for an all-composite full-scale wing box are presented. The wing box is representative of a section of a 220-passenger commercial transport aircraft wing box and was designed and constructed by The Boeing Company as part of the NASA Advanced Subsonics Technology (AST) program. The semi-span wing was fabricated from a graphite-epoxy material system with cover panels and spars held together using Kevlar stitches through the thickness. No mechanical fasteners were used to hold the stiffeners to the skin of the cover panels. Tests were conducted with and without low-speed impact damage, discrete source damage and repairs. Up-bending down-bending and brake roll loading conditions were applied. The structure with nonvisible impact damage carried 97% of Design Ultimate Load prior to failure through a lower cover panel access hole. Finite element and experimental results agree for the global response of the structure.


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    Title :

    Structural Response and Failure of a Full-Scale Stitched Graphite-Epoxy Wing


    Contributors:
    D. C. Jegley (author) / A. E. Lovejoy (author) / H. G. Bush (author)

    Publication date :

    2001


    Size :

    14 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English





    Structural Response and Failure of a Full-Scale Stitched Graphite-Epoxy Wing

    Jegley, Dawn C. / Lovejoy, Andrew E. / Bush, Harold G. | NTRS | 2001


    Structural response and failure of a full-scale stitched graphite-epoxy wing

    Jegley, Dawn / Bush, Harold / Lovejoy, Andrew | AIAA | 2001



    AIAA-2001-1334 Structural Response and Failure of a Full-Scale Stitched Graphite-Epoxy Wing

    Jegley, D. / Bush, H. / Lovejoy, A. et al. | British Library Conference Proceedings | 2001