Loading...
Please wait, while we are loading the content...
Similar Documents
Evaluation of the structural response and failure of a full-scale stitched graphite-epoxy wing
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Jegley, Dawn C. Lovejoy, Andrew E. Bush, Harold G. |
| Copyright Year | 2001 |
| Description | 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. |
| File Size | 1279906 |
| Page Count | 12 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_20030012585 |
| Archival Resource Key | ark:/13960/t23c10m0h |
| Language | English |
| Publisher Date | 2001-01-01 |
| Access Restriction | Open |
| Subject Keyword | Structural Mechanics Finite Element Method Wings Structural Failure Semispan Models Graphite-epoxy Composites Commercial Aircraft Kevlar Trademark Impact Damage Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Article |
