Article ID | Journal | Published Year | Pages | File Type |
---|---|---|---|---|
6706082 | Composite Structures | 2016 | 16 Pages |
Abstract
Carbon-epoxy composite laminate recovery rates are analyzed with respect to their static and fatigue strengths following local-damage repair using the scarf-patch bonding method. The tensile strength recovery rate is tested for 1.9-11.3° scarf angles (scarf ratios: 1/30-1/5). Static tests are performed for three external-ply overlap lengths and two defect sizes. The fatigue characteristics are identified via fatigue testing of a defect-free specimen and two specimens with different scarf angles. The static test results indicate that the strength recovery rate is significantly lower for scarf ratios of 1/10 or greater. Conversely, 1/20 and 1/30 scarf-ratio specimens exhibit high recovery rates of 79.1% and 83.6%, respectively, compared to the defect-free specimen. The external-ply overlap length and defect-size effects are negligible. For a million-cycle fatigue test, the fatigue strength recovery rates of the 1/20 and 1/30 specimens are 39.7% and 52.1%, respectively, being lower than the static strength recovery rate.
Keywords
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Physical Sciences and Engineering
Engineering
Civil and Structural Engineering
Authors
Jae-Seung Yoo, Viet-Hoai Truong, Min-Young Park, Jin-Ho Choi, Jin-Hwe Kweon,