Beneficial Patch Repair Effect on Fatigue Crack Growth of Al-Alloy 7050

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Fatigue problems become an important topic in the maintenance of aircraft structures. Efficient repair technique, called composite patch repair, was used to reinforce the damaged structures and extend the service life. In this paper, using empirical approach, the effect of composite patch repair on fatigue crack growth was investigated on 7050 aluminum alloy. In additional, loading parameters associated with patch repair (Graphite/Epoxy) was studied in order to show their influence on fatigue life and fatigue crack growth rate, namely stress ratio. Results provide an increasing in fatigue life and fatigue crack growth rate in increased stress ratio. A delayed in fatigue life and diminution of FCGRs is the results of composite patch repair. Effect of patch repair was shown highly at high stress intensity factor when maximum applied loading is kept constant.

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Edited by:

R. Varatharajoo, E. J. Abdullah, D. L. Majid, F. I. Romli, A. S. Mohd Rafie and K. A. Ahmad

Pages:

158-164

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M. Benachour et al., "Beneficial Patch Repair Effect on Fatigue Crack Growth of Al-Alloy 7050", Applied Mechanics and Materials, Vol. 225, pp. 158-164, 2012

Online since:

November 2012

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$38.00

[1] B. Bouiadjra, H. Fekirini, B. Serier, M. Belhouari, M. Benguediab, J. Reinf. Plast, Compos. Vol. 27, (2008), p.1135–1146.

[2] A.A. Baker, In: Jones R, Miller NJ, International conference on aircraft damage assessment and repair, Melbourn, Australia, pp.209-215, (1991).

[3] A.A. Baker: Composites Vol. 18 (1987), pp.293-308.

[4] A.A. Baker, L.R.F. Rose and R. Jones, Elsevier Publisher, Amsterdam, (2002).

[5] V. Sabelkin, S. Mall and J.B. Avram, Engineering Fracture Mechanics Vol. 73 (2006), pp.1553-1567.

[6] V. Sabelkin, S. Mall, M.A., Hansen, R.M. Vandawaker and M. Derriso, Composite Structures Vol. 79 (2007), pp.55-66.

DOI: https://doi.org/10.1016/j.compstruct.2005.11.028

[7] C.L. Ong and S.B. Shen, Int. J. of Adhesion & Adhesives, Vol. 12(1) (1992), pp.19-26.

[8] D. Kujawsky, Int. J. of Fatigue Vol. 23 (2001), p.95.

[9] M. Benachour, A. Hadjoui, M. Benguediab and N. Benachour, Materials Research Society Symposium Proceedings Vol. 1276 (2010), pp.55-60.

[10] D.L. Duquesnay, P.R. Underhill, H.J. and Britt, Fatigue Fract. Engng Mater. Struct., Vol. 28 (2005), pp.381-389.

[11] L.P. Borrego, J.M. Costa, F.V. Antunes, J.M. Ferreira, Engineering Failure Analysis, Vol. 17(1) (2010), pp.11-18.

[12] AL. TH. Kermanidis and SP.G. Pantelakis, Fat. Fract. Engng Mat. Struct. Vol. 24 (2001), pp.679-710.

[13] J.H. Kim, S.B. Lee and S.G. Hong, Theor. Appl. Fract. Mech. 40 (2003), pp.135-144.

[14] C.S. Chung, J.K. Kim, H.K. Kim, W.J. Kim, Materials Science and Engineering A Vol. 337(1-2) (2002), pp.39-44.

[15] M.L. Pastor, X. Balandraud, J.L. Robert and M. Grédiac, Int. J. Fatigue Vol. 31 (2009), pp.850-858.

[16] H. Hosseini-Toudeshky, Composite Structures Vol. 76 (2006), pp.243-251.

[17] V. Sinha, C. Mercer, W.O. Soboyejo, Mat. Scie. Engng A Vol. 287 (2000), pp.30-42.

[18] J.C. Jr Newman, In ASTM STP 1149, J. Larson and J.E. Allison, Eds. American Society for Testing and Materials, Philadelphia (1992), pp.6-33.

[19] K. Boyd, S. Krishnan, A. Litvinov, J., Eisner, J. Harter, M. Ratwani, and G. Glinka, Development of structural integrity analysis technologies for aging aircraft structures: Bonded composite patch repair & weight function methods. WL-TR-97-3105, Wright-Patterson AFB, OH, (1997).

[20] J.A. Harter, AFGROW users guide and technical manual - AFGROW for Windows 2K/XP. Version 4. 0011. 14, Air Force Research Laboratory, (2006).

DOI: https://doi.org/10.21236/ada370431