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Damage tolerant composite wing panels for transport aircraft
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Smith, Peter J. Gibbins, M. N. Wilson, Robert D. |
| Copyright Year | 1985 |
| Description | Commercial aircraft advanced composite wing surface panels were tested for durability and damage tolerance. The wing of a fuel-efficient, 200-passenger airplane for 1990 delivery was sized using grahite-epoxy materials. The damage tolerance program was structured to allow a systematic progression from material evaluations to the optimized large panel verification tests. The program included coupon testing to evaluate toughened material systems, static and fatigue tests of compression coupons with varying amounts of impact damage, element tests of three-stiffener panels to evaluate upper wing panel design concepts, and the wing structure damage environment was studied. A series of technology demonstration tests of large compression panels is performed. A repair investigation is included in the final large panel test. |
| File Size | 12652228 |
| Page Count | 60 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19890005816 |
| Archival Resource Key | ark:/13960/t22c3wp9z |
| Language | English |
| Publisher Date | 1985-12-01 |
| Access Restriction | Open |
| Subject Keyword | Composite Materials Structural Members Wings Yield Point Transport Aircraft Mechanical Properties Durability Graphite-epoxy Composites Composite Structures Wing Panels Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Technical Report |
