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An experimental study on the tensile behavior of the cracked aluminum plates repaired by fiber metal laminate (FML) patches

Published online by Cambridge University Press:  08 February 2013

Faramarz Ashenai Ghasemi ,
Ahmad Fallah Rahmatabadi ,
Gholamhassan Payganeh  and
Ali Pourkamali Anaraki
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Abstract

Fiber metal laminates (FMLs) are widely used in aerospace industries nowadays. Repairing of the cracks in these advanced materials was first done by some aeronautical laboratories in early 1970s. In this study, experimental investigations were done on the effect of repairing the center-cracked aluminum plates using the FML patches. The repairing processes were conducted to characterize the response of the repaired structures to tensile tests. The composite patches were made of one aluminum layer and two woven glass-epoxy composite layers. Three different crack lengths in three crack angles and different patch lay-ups were examined. It was observed that no matter what the crack length was, the more the crack angle is larger, the more ultimate tensile strength of the structure became. It was also indicated that the patch lay-up had an important effect on the tensile response of the repaired specimens. When the aluminum layer of the patches was farther from the repair zone, the ultimate tensile strength reached to its maximum value.

Keywords

Fiber metal laminate (FML)repairtensile strengthcrack
Type
Research Article
Information
Mechanics & Industry , Volume 14 , Issue 1 , 2013 , pp. 53 - 58
Copyright
© AFM, EDP Sciences 2013

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References

Références

Qin, R.Y., Schreiber, H.P., Adhesion at partially restructured polymer surfaces, Colloids Surf. A : Physicochem, Eng. Aspects 156 (1999) 85–93 CrossRefGoogle Scholar
R.C. Alderliesten, Fatigue, In Fibre metal laminates : an introduction, ed. A. Vlot, J.W. Gunnink, Kluwer Academic Publishers, Dordrecht, 2001, pp. 155–171
Guocai, Wu, Yang, Jenn-Ming, The mechanical behaviour of GLARE laminates for aircraft structures, J. Minerals Mater. Soc. 57 (2005) 72–79 Google Scholar
Hagenbeek, M., Van Hengel, C., Bosker, O.J., Vermeeren, C.A.J.R., Static properties of fibre metal laminates, Appl. Compos. Mater. 10 (2003) 207–222 CrossRefGoogle Scholar
Homan, J.J., Fatigue initiation in fibre metal laminates, Int. J. Fatigue 28 (2006) 366–374 CrossRefGoogle Scholar
Chang, Po-Yu, Yang, Jenn-Ming, Seo, Hyoung-seock, Hahn, H.T., Off-axis fatigue cracking behavior in notched fiber metal laminates, Fatigue Fracture Eng. Mater. Struct. 30 (2007) 1158–1171 CrossRefGoogle Scholar
Po-Yu Chang, Po-Ching Yeh, Jenn-Ming Yang, Static behavior of notched and un-notched fiber metal laminates with hybrid boron/glass fibers, Modeling and Simulation in Materials Science and Engineering, 2008, submitted
Clearfield, H.M., McNamara, D.K., Davis, G.D., In Engineered materials handbook, Adhesives and sealants, ed. H.F. Brinson, ASM Inter. 3 (1990) 260 Google Scholar
Hosseini-Toudeshky, H., Mohammadi, B., Bakhshandeh, S., Crack trajectory analysis of single-side repaired thin panels in mixed-mode conditions using glass/epoxy patches, Comp. Struct. 86 (2008) 997–1005 CrossRefGoogle Scholar
ASTM D 2651, American Society for Testing and Materials (ASTM), West Consnohocken, USA, 1995 Standard guide for preparation of metal surfaces for adhesive bonding
Huntsman Advanced materials data sheet for Araldite LY5052-1 /Aradure 5052-1, www.huntsman.com/advanced_materials, 2007
Advanced materials data sheet for Araldite 2015, www.huntsman.com/advanced_materials, April 2007
R.F. Wegman, Surface preparation techniques for adhesive bonding. William Andrew Inc. Noyes Publication, 1989
www.instron.com
Chukwujekwu Okafor, A., Singh, N., Enemuoh, U.E., Rao, S.V., Design, analysis and performance of adhesively bonded composite patch repair of cracked aluminum aircraft panels, Compos. Struct. 71 (2005) 258–270 CrossRefGoogle Scholar