| Full text | |
| Author(s): |
Total Authors: 2
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| Affiliation: | [1] Aeronaut Inst Technol, Dept Aeronaut, Sao Jose Dos Campos - Brazil
Total Affiliations: 1
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| Document type: | Journal article |
| Source: | ENGINEERING FRACTURE MECHANICS; v. 235, AUG 1 2020. |
| Web of Science Citations: | 0 |
| Abstract | |
A cohesive zone model is proposed to analyse composite delamination propagation under high-cycle fatigue loading. A new method to compute the strain energy release rate at any point within the element fatigue life cycle range is presented. The proposed scheme is based on the J-integral method evaluated at an estimated position of the crack-tip within the element, instead of the element integration points. Furthermore, a new fatigue damage evolution law is proposed to account for the unwanted quasi-static damage during the element fatigue degradation process. The model prediction capabilities were verified against experimental data available in the literature and theoretical solutions using a double cantilever beam configuration for mode I loading, four-point end-notched flexure configuration for mode II loading, and mixed-mode bending configuration for mixed-mode loading. The simulations were performed at both constant and variable amplitude loading. The numerical predictions obtained using the proposed model correlated very well with literature's experimental data. (AU) | |
| FAPESP's process: | 15/16733-2 - Modelling of bonded joints in composite material structures for aeronautic applications |
| Grantee: | Mariano Andrés Arbelo |
| Support Opportunities: | Scholarships in Brazil - Post-Doctoral |