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Behavior of compression-loaded composite panels with stringer terminations and impact damage
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Jegley, Dawn C. |
| Copyright Year | 1998 |
| Description | The results of an analytical and experimental study of graphite-epoxy stiffened panels with impact-damaged stringer terminations are presented. Five stitched graphite-epoxy panels with stiffeners with a gradual reduction in either thickness or height were examined. Panels were analyzed using finite element analysis and tested by loading them in axial compression to a predetermined load. The panels were then subjected to impact damage and loaded to failure. Axial midplane strains, surface strains, interlaminar strains and failure results are discussed. |
| File Size | 389292 |
| Page Count | 12 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_20040087397 |
| Archival Resource Key | ark:/13960/t7hq8w74g |
| Language | English |
| Publisher Date | 1998-01-01 |
| Access Restriction | Open |
| Subject Keyword | Structural Mechanics Panels Failure Modes Compression Loads Skin Structural Member Commercial Aircraft Axial Strain Finite Element Method Thickness Nonlinearity Graphite-epoxy Composites Composite Structures Impact Damage Stringers Ntrs Nasa Technical Reports ServerĀ (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Article |