Fatigue crack growth of bonded composite repairs in gigacycle regime

Q. Y. Wang; M. R. Sriraman; N. Kawagoishi; Q. Chen

doi:10.1016/j.ijfatigue.2006.02.028

Fatigue crack growth of bonded composite repairs in gigacycle regime

Q. Y. Wang, M. R. Sriraman, N. Kawagoishi, Q. Chen

研究成果: Contribution to journal › Article › 査読

13 被引用数 (Scopus)

抄録

Fatigue induced from various aeromechanical sources can reach gigacycle regime due to vibratory stress cycles at high frequencies. Composite repairs offer various advantages over mechanical fastening or riveting, including improved long-term durability behavior and reduced corrosion. In this study, by using ultrasonic frequency cyclic loading, fatigue crack growth tests in gigacycle regime were conducted on notched 7075 and 6061 aluminum alloy substrates (in T6 condition) with and without bonded Boron/epoxy patches. A considerable increase in the fatigue life was observed with more number of patch plies. The effect of patch configuration and thickness on enhancing the fatigue strength by orders of magnitude has been demonstrated.

本文言語	英語
ページ（範囲）	1197-1201
ページ数	5
ジャーナル	International Journal of Fatigue
巻	28
号	10 SPEC. ISS.
DOI	https://doi.org/10.1016/j.ijfatigue.2006.02.028
出版ステータス	出版済み - 10 2006
外部発表	はい

All Science Journal Classification (ASJC) codes

Modelling and Simulation
Materials Science(all)
Mechanics of Materials
Mechanical Engineering
Industrial and Manufacturing Engineering

文献へのアクセス

10.1016/j.ijfatigue.2006.02.028

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引用スタイル

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abstract = "Fatigue induced from various aeromechanical sources can reach gigacycle regime due to vibratory stress cycles at high frequencies. Composite repairs offer various advantages over mechanical fastening or riveting, including improved long-term durability behavior and reduced corrosion. In this study, by using ultrasonic frequency cyclic loading, fatigue crack growth tests in gigacycle regime were conducted on notched 7075 and 6061 aluminum alloy substrates (in T6 condition) with and without bonded Boron/epoxy patches. A considerable increase in the fatigue life was observed with more number of patch plies. The effect of patch configuration and thickness on enhancing the fatigue strength by orders of magnitude has been demonstrated.",

author = "Wang, {Q. Y.} and Sriraman, {M. R.} and N. Kawagoishi and Q. Chen",

note = "Funding Information: The authors are grateful for the support of National Science Foundation of China through Grant NSFC-10372064 and the Specialized Research Fund for the Doctoral Program of Chinese Higher Education through Grant 20030610001. ",

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AU - Wang, Q. Y.

AU - Sriraman, M. R.

AU - Kawagoishi, N.

AU - Chen, Q.

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AB - Fatigue induced from various aeromechanical sources can reach gigacycle regime due to vibratory stress cycles at high frequencies. Composite repairs offer various advantages over mechanical fastening or riveting, including improved long-term durability behavior and reduced corrosion. In this study, by using ultrasonic frequency cyclic loading, fatigue crack growth tests in gigacycle regime were conducted on notched 7075 and 6061 aluminum alloy substrates (in T6 condition) with and without bonded Boron/epoxy patches. A considerable increase in the fatigue life was observed with more number of patch plies. The effect of patch configuration and thickness on enhancing the fatigue strength by orders of magnitude has been demonstrated.

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