Abstract
The compression modulus and compression strength of a proprietary ultra-high modulus carbon/epoxy composite are experimentally determined using SACMA SRM 1R-94 and ASTM D6641 for laminates with stacking sequences of [(0/ ± 60)s]2 and [(+60/0/-60)s]2. The moduli of both laminates are experimentally shown to be statistically equivalent; the strength of the [(0/ ± 60)s]2 laminate is shown to be significantly less than the [(+60/0/-60)s]2 laminate. A finite element model is developed for each compression test to predict the compression modulus and compression strength using the built-in damage progression algorithm in Abaqus. Premature end crushing is predicted in the modulus specimen of SACMA SRM 1R-94 for the [(+60/0/60)s]2 laminate. End crushing in the modeled SACMA SRM 1R-94 strength specimen is predicted to occur immediately after ultimate laminate failure for the [(+60/0/60)s]2 laminate. Fiber misalignment is found to significantly affect the predicted compression modulus and compression strength of the ultra-high modulus carbon/epoxy composite analyzed.
| Original language | English (US) |
|---|---|
| Pages (from-to) | 701-712 |
| Number of pages | 12 |
| Journal | Journal of Composite Materials |
| Volume | 50 |
| Issue number | 5 |
| DOIs | |
| State | Published - Mar 1 2016 |
All Science Journal Classification (ASJC) codes
- Ceramics and Composites
- Mechanics of Materials
- Mechanical Engineering
- Materials Chemistry