Abstract
Edge delamination in composite laminates is analyzed using a closed form, crack tip element approach. Classical laminated plate theory is utilized for the crack tip element formulation. Energy release rates and fracture mode ratios as found by this new approach are shown to agree with finite element results for mechanical, hygrothermal, and combined loadings. For those cases where a linear elastic solution predicts a near-field oscillatory singularity, a relatively simple method is proposed that allows a unique value of fracture mode ratio to be defined.
| Original language | English (US) |
|---|---|
| Pages (from-to) | 155-175 |
| Number of pages | 21 |
| Journal | ASTM Special Technical Publication |
| Issue number | 1230 |
| State | Published - Oct 1995 |
| Event | Proceedings of the 5th Symposium on Composite Materials: Fatigue and Fracture - Atlanta, GA, USA Duration: May 4 1993 → May 6 1993 |
ASJC Scopus subject areas
- General Engineering