Analytical and experimental results 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. Upbending, 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 :

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


    Contributors:

    Conference:

    AHS Structures Specialists'' Meeting ; 2001 ; Williamsburg, VA, United States


    Publication date :

    2001-01-01


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English




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

    D. C. Jegley / A. E. Lovejoy / H. G. Bush | NTIS | 2001



    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