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Interlaminar fracture toughness of thermoplastic composites
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Johnston, N. J. Obrien, T. K. Hinkley, J. A. |
| Copyright Year | 1988 |
| Description | Edge delamination tension and double cantilever beam tests were used to characterize the interlaminar fracture toughness of continuous graphite-fiber composites made from experimental thermoplastic polyimides and a model thermoplastic. Residual thermal stresses, known to be significant in materials processed at high temperatures, were included in the edge delamination calculations. In the model thermoplastic system (polycarbonate matrix), surface properties of the graphite fiber were shown to be significant. Critical strain energy release rates for two different fibers having similar nominal tensile properties differed by 30 to 60 percent. The reason for the difference is not clear. Interlaminar toughness values for the thermoplastic polyimide composites (LARC-TPI and polyimidesulfone) were 3 to 4 in-lb/sq in. Scanning electron micrographs of the EDT fracture surfaces suggest poor fiber/matrix bonding. Residual thermal stresses account for up to 32 percent of the strain energy release in composites made from these high-temperature resins. |
| File Size | 29514182 |
| Page Count | 33 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19880012713 |
| Archival Resource Key | ark:/13960/t0cv9d875 |
| Language | English |
| Publisher Date | 1988-02-01 |
| Access Restriction | Open |
| Subject Keyword | Composite Materials Interlayers Laminates Cantilever Beams Edges Polyimide Resins Interfaces Thermoplastic Resins Carbon Fibers Delaminating Fracture Strength Thermal Stresses Residual Stress Resin Matrix Composites 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 |
