Effect of Curing Cycle on Fatigue Life of Cracked AA7075-T6 Aircraft Sheet Repaired with a Boron/Epoxy Composite Patch
Author:
Publisher
Springer Science and Business Media LLC
Subject
Mechanical Engineering,Mechanics of Materials,Computational Mechanics
Link
https://link.springer.com/content/pdf/10.1007/s40997-020-00400-6.pdf
Reference47 articles.
1. Adams RD, Wake WC (1984) Structural adhesive joints in engineering. Elsevier, London
2. Albedah A et al (2018) Effects of adhesive disbond and thermal residual stresses on the fatigue life of cracked 2024-T3 aluminum panels repaired with a composite patch. Int J Adhes Adhes 87:22–30
3. Alderliesten RC (2009) Damage tolerance of bonded aircraft structures. Int J Fatigue 31:1024–1030
4. ASTM International (2013) ASTM E647 − 13´1, Standard test method for measurement of fatigue crack growth rates
5. Baker AA, Jones R (1988) Bonded Repair of Aircraft Structures. Springer, Berlin
Cited by 2 articles. 订阅此论文施引文献 订阅此论文施引文献，注册后可以免费订阅5篇论文的施引文献，订阅后可以查看论文全部施引文献
1. Study of the Effects of Adhesive Damage and Plasticity on the Repair of Cracked Aluminum Structures;Journal of Failure Analysis and Prevention;2023-07-11
2. Effect of the stiffness ratio on the growth of repaired fatigue cracks with composite patch;Mechanics Based Design of Structures and Machines;2023-03-28
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