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Lamination residual stresses in hybrid composites, part 1
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Liber, T. Daniel, I. M. |
| Copyright Year | 1976 |
| Description | An experimental investigation was conducted to study lamination residual stresses for various material and loading parameters. The effects of hybridization on residual stresses and residual properties after thermal cycling under load were determined in angle-ply graphite/Kevlar/epoxy and graphite/S-glass/epoxy laminates. Residual strains in the graphite plies are not appreciably affected by the type and number of hybridizing plies. Computed residual stresses at room temperature in the S-glass plies reach values up to seventy-five percent of the transverse strength of the material. Computed residual stresses in the graphite plies exceed the static strength by approximately ten percent. In the case of Kevlar plies, computed residual stresses far exceed the static strength indicating possible early failure of these plies. Static testing of the hybrids above indicates that failure is governed by the ultimate strain of the graphite plies. In thermally cycled hybrids, in general, residual moduli were somewhat lower and residual strengths were higher than initial values. |
| File Size | 4250803 |
| Page Count | 169 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19770004171 |
| Archival Resource Key | ark:/13960/t2c872x1k |
| Language | English |
| Publisher Date | 1976-06-01 |
| Access Restriction | Open |
| Subject Keyword | Composite Materials Thermal Cycling Tests Thermodynamic Properties Laminates Residual Stress Static Loads Static Tests 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 |
