期刊
JOURNAL OF ADHESION
卷 98, 期 4, 页码 367-389出版社
TAYLOR & FRANCIS LTD
DOI: 10.1080/00218464.2020.1834389
关键词
Compoiste structure; scarf repair; fatigue mechanism; fatigue life; reliability and confi dence level
资金
- National Natural Science Foundation of China [11672238]
- National Natural Science Foundation for Young Scientists of China [71701021]
- Natural Science Basic Research Plan in Shaanxi Province of China [2017JM1027]
- Overseas Expertise Introduction Project for Discipline Innovation (the 111 Project) [BP0719007]
This paper focuses on the fatigue performances and reliability analysis of scarf-repaired carbon fiber composite laminates. Experimental results show the fatigue limit of scarf-repaired composite laminates and the dominant failure mode. The distribution of fatigue life data is also discussed.
This paper focuses on the fatigue performances and reliability analysis of fatigue life for scarf-repaired carbon fiber composite laminates, which plays an important role in ensuring the safety of repaired aircraft. Tension-tension fatigue tests at constant-load amplitude were conducted to determine the fatigue limit and mechanism of scarf-repaired composite laminates. Experimental results show that the fatigue limit of scarf-repaired composite laminates is about 34% of the static tensile strength and the failure modes of speicmens under different stress levels are similar. The dominated failure mode is cohesive failure of adhesive, accompanied by partial 45 degrees and 90 degrees matrix cracks of composite patch. Meanwhile, the stiffness degradation and crack observation indicate that the crack initiation stage occupies a large proportion (92 +/- 5%) of fatigue life. In additon, the distribution of fatigue life data was discussed. Based on the best fitting distribution, a new approach incorporating both reliability and con?dence level was proposed to predict the fatigue life of scarf-repaired composites.
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