A study on the fatigue crack growth behavior of thick aluminum panels repaired with a composite patch

Chung, Ki-Hyun; Yang, Won-Ho

doi:10.1016/s0263-8223(02)00338-0

Cited by 29 publications

(17 citation statements)

References 10 publications

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“…Chung et al [5] performed experimental investigations on the effect of composite material patch repairing to characterize the fatigue crack growth behavior in a thick Al6061-T6 (6 mm) panels with a single-sided fiber-reinforced composite patch. They showed that the fatigue life of patched plate increases about 4-6 times compared to the un-patched plate.…”

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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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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“…F. Benyahia et al [14] investigated the fatigue life of 7075 T6 aluminum alloy repaired with composite patch, and in their study, they found that the stress intensity factors (SIF) at the crack tip had a significantly decrease because of the presence of the patch. Ki-Hyun Chung and Won-Ho Yang [15] investigated the effect of composite patch lengths on the fatigue crack growth behavior in Al 6061-T6 panels with one-sided fiber reinforced composite patches. The results had shown that the sizes of composite patch could affect the fatigue life.…”

Section: Introductionmentioning

confidence: 99%

Fatigue behavior of thick center cracked aluminum plates repaired by two-sided composite patching

Hao

2015

Materials & Design

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“…4 Generally, thin panels were analyzed by using 2-D models, [5][6][7][8][9][10][11][12][13] whereas thick panels were done as a 3-D problem. [14][15][16][17][18][19][20][21][22][23][24] With thin panels, Naboulsi and Mall 5 proposed a 2-D model for the analysis of adhesive layer, composite patch and thin notched substrate panel. Sun and Klug 6 developed an effective spring model of adhesive layer from the Mindlin plate theory.…”

Section: Introductionmentioning

confidence: 99%

“…Though the 3-D FE analysis has been employed to calculate stress intensity factors at the tip of a crack in repaired panels, no numerical analysis has been conducted to simulate crack growth process. [20][21][22][23] A combination of BE model and FE method (BEM/FEM) has been presented by Sekine et al 24 to determine stress intensity factor. Oudad et al 25 investigated the influences of mechanical properties of adhesive layer and composite patch as well as crack depth on plastic zone size of crack tip in by using 3-D non-linear FEA.…”

Section: Introductionmentioning

confidence: 99%

Material parameter modeling and solution technique using birth–death element for notched metallic panel repaired with bonded composite patch

Tong

Shi-qiu

Xiong

2014

Chinese Journal of Aeronautics

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This paper seeks to outline a novel three-layer model and a new birth-death element solution technique to evaluate static strength of notched metallic panel repaired with bonded composite patch and to optimize material parameters. The higher order 3D, 8-node isotropic solid element and 8-node anisotropic layered solid element with three degrees of freedom per node are respectively implemented to model substrate panel, adhesive layer and composite patch to establish three-layer model of repaired panel. The new solving technique based on birth-death element is developed to allow solution of the stress pattern of repaired panel for identifying failure mode. The new model and its solution are used to model failure mode and residual strength of repaired panel, and the obtained results have a good agreement with the experimental findings. Finally, the influences of material parameter of adhesive layer and composite patch on the residual strength of repaired panel are investigated for optimizing material properties to meet operational and environmental constraints.

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A study on the fatigue crack growth behavior of thick aluminum panels repaired with a composite patch

Cited by 29 publications

References 10 publications

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

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

Fatigue behavior of thick center cracked aluminum plates repaired by two-sided composite patching

Material parameter modeling and solution technique using birth–death element for notched metallic panel repaired with bonded composite patch

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