EVALUATION OF THE STRUCTURAL RESPONSE AND FAILURE OF A FULL-SCALE STITCHED GRAPHITE-EPOXY WING

摘要

Analytical and experimental results for an all-composite full-scale wing box are presented.rnThe wing box is representative of a section of a 220-passenger commercial transport aircraft wing boxrnand was designed and constructed by The Boeing Company as part of the NASA Advanced SubsonicsrnTechnology (AST) program. The semi-span wing was fabricated from a graphite-epoxy materialrnsystem with cover panels and spars held together using Kevlar stitches through the thickness. Nornmechanical fasteners were used to hold the stiffeners to the skin of the cover panels. Tests werernconducted with and without low-speed impact damage, discrete source damage and repairs. Upbending,rndown-bending and brake roll loading conditions were applied. The structure with nonvisiblernimpact damage carried 97% of Design Ultimate Load prior to failure through a lower cover panelrnaccess hole. Finite element and experimental results agree for the global response of the structure.