期刊
COMPOSITE STRUCTURES
卷 140, 期 -, 页码 417-432出版社
ELSEVIER SCI LTD
DOI: 10.1016/j.compstruct.2015.12.041
关键词
Composite; Scarf patch repair; Strength recovery
资金
- Advanced Scarf Repair Method and Equipment Development for Aircraft MRO through the Ministry of Trade, Industry and Energy [R0004399-2]
- Agency for Defense Development [UE140513JD]
- National Research Foundation of Korea [21A20131712492] Funding Source: Korea Institute of Science & Technology Information (KISTI), National Science & Technology Information Service (NTIS)
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 degrees 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. (C) 2016 Elsevier Ltd. All rights reserved.
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