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Prediction of composite laminate fracture: micromechanics and progressive fracture
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Minnetyan, L. Gotsis, P. K. Chamis, C. C. |
| Copyright Year | 1996 |
| Description | This report describes an investigation to predict first-ply failure and final fracture in selected composite laminates subjected to inplane loads. The laminates were composed of glass fiber and graphite fibers in epoxy matrices. Failure envelopes based on first-ply failure and laminate fracture were generated for combined loading of these laminates. Predictions were evaluated by micromechanics-based theory and progressive fracture. The results show that, for most cases, combined tensile loading significantly enhanced the laminate fracture stress in comparison to the uniaxial loading. |
| File Size | 846948 |
| Page Count | 18 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19970010089 |
| Archival Resource Key | ark:/13960/t74v1j862 |
| Language | English |
| Publisher Date | 1996-12-01 |
| Access Restriction | Open |
| Subject Keyword | Structural Mechanics Micromechanics Epoxy Matrix Composites Stress-strain Relationships Graphite-epoxy Composites Laminates Residual Stress Matrix Materials Fracturing Glass Fibers Loads Forces 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 |
