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Test and analysis of a stitched rfi graphite-epoxy panel with a fuel access door
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Jegley, Dawn C. Waters Jr., W. Allen |
| Copyright Year | 1994 |
| Description | A stitched RFI graphite-epoxy panel with a fuel access door was analyzed using a finite element analysis and loaded to failure in compression. The panel was initially 56-inches long and 36.75-inches wide and the oval access door was 18-inches long and 15-inches wide. The panel was impact damaged with impact energy of 100 ft-lb prior to compressive loading; however, no impact damage was detectable visually or by A-scan. The panel carried a failure load of 695,000 Ib and global failure strain of .00494 in/in. Analysis indicated the panel would fail due to collapse at a load of 688,100 Ib. The test data indicate that the maximum strain in a region near the access door was .0096 in/in and analysis indicates a local surface strain of .010 in/in at the panel's failure load. The panel did not fail through the impact damage, but instead failed through bolt holes for attachment of the access door in a region of high strain. |
| File Size | 4428399 |
| Page Count | 54 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19940024597 |
| Archival Resource Key | ark:/13960/t3xt0n30g |
| Language | English |
| Publisher Date | 1994-03-01 |
| Access Restriction | Open |
| Subject Keyword | Composite Materials Collapse Finite Element Method Panels Structural Failure Failure Analysis Compression Loads Bolts Graphite-epoxy Composites Resins Impact Damage Holes Mechanics 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 |
