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

摘要

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 program. The semispan wing was fabricated from a graphite-epoxy material system with cover panels and spars held together using Kevlar~(~R) 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, downbending, and brake roll loading conditions were applied. The structure with nonvisible impact damage carried 97% of design ultimate load before failure through a lower cover panel access hole. Finite element and experimental results agree for the global response of the structure.