Fatigue crack propagation of aluminium panels repaired with adhesively bonded composite laminates

Daghyani, Hamid Reza; Sayadi, Ali A.; Hosseini, Hooman

doi:10.1177/146442070321700405

Cited by 6 publications

(4 citation statements)

References 4 publications

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“…Crack repair using laser welding Baker and Jones (1988) recognized reinforcing cracked aluminum structures with composite patches as an efficient and economical method to extend the service life of cracked aluminum components. Sun et al (1996) and Daghyani et al (2003) investigated the strength and crack propagation of reinforced cracked aluminum structures with composite patches. To further enhance the effectiveness of composite patches, it is envisioned that the crack can be first fused by laser welding, to remove the high stress concentration at the crack front, before applying the composite patch (Sun, 2008).…”

Section: Fatigue Cracksmentioning

confidence: 99%

Fatigue crack fusion in thin-sheet aluminum alloys AA7075-T6 using low-speed fiber laser welding

Paleocrassas

2011

Journal of Materials Processing Technology

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Section: Fatigue Cracksmentioning

confidence: 99%

Fatigue crack fusion in thin-sheet aluminum alloys AA7075-T6 using low-speed fiber laser welding

Paleocrassas

2011

Journal of Materials Processing Technology

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“…Reinforcing cracked aluminium structures with composite patches has been recognized as an efficient and economical method to extend the service life of cracked aluminium components (Baker and Jones, 1988;Sun et al, 1996;Daghyani et al, 2003). To further enhance the effectiveness of composite patches, it is envisioned that the crack can be first fused by laser welding to remove the high stress concentration at the crack front before applying the composite patch (Sun, 2008).…”

Section: Applications To Aluminium Fatigue Crack Repairmentioning

confidence: 99%

Low Speed Laser Welding of Aluminium Alloys Using Single-Mode Fiber Lasers

Tu¹,

Paleocrassas²

2010

Laser Welding

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Background and Reviews Aluminium AlloysAluminium alloys can be separated into two major categories: Non heat-treatable and heattreatable. The initial strength of non heat-treatable alloys depends primarily upon the hardening effect of alloying elements such as silicon, iron, manganese and magnesium. The non heat-treatable alloys are mainly found in 1xxx, 3xxx, 4xxx and 5xxx series. Additional strength is usually achieved by solid-solution strengthening or strain hardening. The initial strength of heat-treatable alloys depends upon the alloy composition, just like the non heat-treatable alloys. In order to improve their mechanical properties they need to undergo solution heat treating and quenching followed by either natural or artificial aging (precipitation hardening). This treatment involves maintaining the work piece at an elevated temperature, followed by controlled cooling in order to achieve maximum hardening. The heat-treatable alloys are found primarily in the 2xxx, 6xxx and 7xxx alloy series (ibid). The 7xxx series alloys contain zinc in amounts between 4 and 8 % and magnesium in amounts between 1 and 3 %. Both have high solid solubility in aluminium. The addition of www.intechopen.com Low speed laser welding of aluminium alloys using single-mode iber lasers 49 magnesium produces a marked increase in precipitation hardening characteristics. Copper additions between 1 and 2 % increase the strength by solid solution hardening, and form the basis of high strength aircraft alloys. The addition of chromium, typically up to 0.3 %, improves stress corrosion cracking resistance. The 7xxx series alloys are predominantly used in aerospace applications, 7075-T6 being the principal high strength aircraft alloy (Ion, 2000). This chapter will focus on fiber laser welding of 7075-T6 because of its predominant use in aircraft components.

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“…5 A cohesive law was developed for investigating fatigue crack growth of aluminium panels repaired with adhesively bonded composite laminates. 6 A cohesive zone model was developed for delamination propagation of a composite under cyclic loadings. 7 For ductile materials, a cohesive fracture model based on necking was developed.…”

Section: Introductionmentioning

confidence: 99%

Softening behaviour modelling of aluminium alloy 6082 using a non-linear cohesive zone law

Kim

2014

Proceedings of the Institution of Mechanical Engineers, Part L:

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A non-linear cohesive zone model is developed for predicting stress–strain behaviour of unnotched aluminium alloys. A uniform cohesive layer is added into the middle of a dogbone-type specimen. Mechanical properties of aluminium alloy 6082 are used as those of a cohesive layer; Voce equation is used for describing the softening behaviour of heat treated and non-heat treated plates. Damage state of a cohesive zone due to tensile loading is evaluated with the damage variable expressed as a function of strain. Predicted engineering stress–strain curves are directly compared with experimental ones. Results show that a proposed model provides the prediction of stress–strain behaviour of aluminium alloys.

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Fatigue crack propagation of aluminium panels repaired with adhesively bonded composite laminates

Cited by 6 publications

References 4 publications

Fatigue crack fusion in thin-sheet aluminum alloys AA7075-T6 using low-speed fiber laser welding

Fatigue crack fusion in thin-sheet aluminum alloys AA7075-T6 using low-speed fiber laser welding

Low Speed Laser Welding of Aluminium Alloys Using Single-Mode Fiber Lasers

Softening behaviour modelling of aluminium alloy 6082 using a non-linear cohesive zone law

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