Investigation into cracked aluminum plate repaired with bonded composite patch

Sabelkin, V.; Mall, S.; Hansen, Michael A.; Vandawaker, Robert M.; Derriso, Mark M.

doi:10.1016/j.compstruct.2005.11.028

Cited by 44 publications

(22 citation statements)

References 24 publications

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“…The debonding pattern around the crack was also investigated by them. Lee et al [18], Hosseini-Toudeshky [19] and Sabelkin et al [20] investigated single-side repaired aluminium plates. When single-side repair is used the crack growth rate would become slower on the repaired side compared to the unrepaired face, creating a non-uniform beach mark on the crack front.…”

Section: Introductionmentioning

confidence: 99%

“…Baker [15], Cheuk et al [16] Colombi et al [17], Lee et al [18], Hosseini-Toudeshky [19], Sabelkin et al [20], Liu et al [6] Taljsten et al [9] and Wu et al [8] have all investigated the patch repair technique in retrofitting of steel or aluminium plates. Tensile fatigue testing of notched plates is a common test performed by these researchers.…”

Section: Introductionmentioning

confidence: 99%

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Effect of prestressed CFRP patches on crack growth of centre-notched steel plates

Emdad

Al-Mahaidi

2015

Composite Structures

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Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Effect of prestressed CFRP patches on crack growth of centre-notched steel plates

Emdad

Al-Mahaidi

2015

Composite Structures

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“…This shift in the stress intensity factor will vary through the thickness of the bonded structure, particularly if a strap is fixed on one side only [13,14]. Thermal residual stresses during the composite bonding process can be reduced by lowering the curing temperature of the adhesive, but lowering the curing temperature will result in longer processing cycles which increases production cost and also reduces the glass transition temperature of the adhesive [15], which then limits the maximum operating temperature.…”

Section: Introductionmentioning

confidence: 96%

Effect of impact damage on fatigue performance of structures reinforced with GLARE bonded crack retarders

Syed

Moffatt

Doucet

et al. 2015

International Journal of Fatigue

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a b s t r a c tFibre-Metal Laminates (FML) such as GLARE are of interest as bonded crack retarders (BCR) to improve the fatigue performance of aircraft structures. The degradation of the performance of the crack retarder in service if subjected to damage is a critical factor in designing with this concept. Bonded assemblies of an aluminium alloy substrate reinforced with a GLARE strap were prepared, and were subjected to low velocity impact damage onto the GLARE, with impact energies ranging from 10 to 60 J. The thermal residual stresses developed during the bonding process of the GLARE to the aluminium were determined using neutron diffraction, and the change in the thermal residual stresses owing to impact damage onto the GLARE was evaluated. Pre-and post-impact fatigue performance of the BCR assemblies has been investigated. The results show that the BCR provides an improvement in fatigue life, but the reduction is impaired following impact damage. The results show that monitoring of impact damage will be critical in the damage tolerance assurance for aerospace structures containing bonded crack retarders.

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“…They also showed that the maximum skin stress for the patched specimen was reduced by 83-85% from that of the un-patched specimen. Sabelkin et al [7] studied several parameters/factors related to mechanical and fatigue behaviors of a cracked 7075-T6 aluminum panel repaired with one-sided adhesively bonded composite patch by a combined experimental-analytical approach. They showed that the disbond does not affect the out-of-plane deformation and in-plane strain except in their vicinity.…”

Section: Introductionmentioning

confidence: 99%

A Study on the Charpy Impact Response of the Cracked Aluminum Plates Repaired with FML Composite Patches

Ghasemi

Vanani

Anaraki

2016

J Fail. Anal. and Preven.

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Fiber metal laminates (FMLs) are widely used in aerospace industries nowadays. Reparation of the cracks in these advanced materials was first done by some aeronautical laboratories in the early 1970s. In this study, experimental investigations were done on the effects of repairing the edge-cracked aluminum plates using the FML patches. The repairing processes were conducted to characterize the response of the repaired structures to the Charpy impact tests. The composite patches were made of one aluminum layer and two woven glass-epoxy composite layers. Three different crack lengths, crack angles, and patch lay-ups were examined. It was indicated that for the lengthen cracks, the effect of increasing the crack angle on energy absorption in the structure was more. When the ratio of crack length to the specimen width, i.e., a/w, is 0.5, the energy absorption per unit area of the specimens having different crack angles but the same patch lay-ups was so different. It was also observed that the percentage of the absorbed energy of 45°cracked angle specimens was about 25% higher than the 0°ones. Also it was observed that the lay-up of the patches and the place where the metal layer was embedded in the FML patches had an important effect on the impact response of the tested specimens. The more the metal layer of the patches is far from the interfacial surface of the aluminum plate and the FML patches, the less the energy absorbs in the structure.

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Investigation into cracked aluminum plate repaired with bonded composite patch

Cited by 44 publications

References 24 publications

Effect of prestressed CFRP patches on crack growth of centre-notched steel plates

Effect of prestressed CFRP patches on crack growth of centre-notched steel plates

Effect of impact damage on fatigue performance of structures reinforced with GLARE bonded crack retarders

A Study on the Charpy Impact Response of the Cracked Aluminum Plates Repaired with FML Composite Patches

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