Evaluation of the Stress Intensity Factor in a Structure Repaired with an Elliptical Composite Patch
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The process of repairing structures by composite materials having various advantages. This method has received much attention from researchers and engineers. In this study, the finite element method is used to analyze the behaviour of a central crack repaired by bonded boron/epoxy composite patch by computing the stress intensity factor at the crack tip. The effects of mechanical and geometrical properties on the behaviour of the structure are highlighted. The results show that the stress intensity factor at the crack tip repaired by an elliptical patch is reduced to 5 % with regard to the repaired by a circular patch.
The reduction obtained by using a boron/epoxy of fibers perpendicular to the crack is more important compared to the same patch having its fibers parallel to the repaired crack. The adhesive properties must be optimised to increase the performance of the patch repair or reinforcement
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A. A. Baker, R. Jones, Bonded Repair of Aircraft Structures (Martinus Nijhoff, Dordrecht, 1988).
S. N. Atluri, Structural Integrity & Durability (Tech. Science Press, Georgia, USA, 1997).
H.H. Toudeshky, B.Mohammadi, H.R.Daghyani, Mixed mode fracture analysis of aluminium repaired panels using composites patches. J. Composites science and technology. 66, 2006, 188-198.
J.C.Klug, C.T.Sun, Large deflection effects of cracked aluminium plates repaired with bonded composite patches. 42 (1998) 291-296.
W. T. Chow, S. N. Atluri, Composite patch repairs of metal structures: adhesive nonlinearity, thermal cycling and debonding. AIAA J. 35(9),1997,1528–1535.
M. R. Lena, J. C. Klug, C. T. Sun, Composite patches as reinforcements and crack arrestors in aircraft structures. J. Aircraft 35(2), 1998,318–323.
A. A. Baker, Repair of cracked or defective metallic aircraft components with advanced fibre composites. An overview of Australian work. Composite Structures. 1984, 153-1581.
A. A. Baker, & R. J. Chester, Recent advances in composite repair technology for metallic aircraft components, Proceedings of International Conference on Advanced Composite Materials. pp 45-49, 1993.
A. A. Baker, Growth characterisation of fatigue cracks repaired with adhesively bonded boron/epoxy patches, Proceedings of International Conference on Fracture, ICF-9, 117-128, 1997.
B. Bachir, L. Belhouari & B. Serier, Computation of the stress intensity factor for repaired cracks in mode I and mixed mode. Composite Structures. 54, 2002, 401-406.
T. Ting, R. Jones, W. K. Chiu, I. H. Marshal & J. M. Greer, Composite repairs to rib stiffened panel, Comp. Struct., 47, 1999, 737-743.
R. J. Callinan, L. R. F. Rose & C. H. Wang, Three dimensional stress analysis of crack patching, Proceedings of International Conference on Fracture, ICF-9, 2151-8, 1997.
R. Jones, W. K. Chiu, Composite repairs to crack in metallic components, Composite Structures, 62 (1999) 431-443.
V. R. S. Turaga & S. Ripidiman, Modelling of patch repairs to a thin cracked sheet, Eng. Fract. Mec., 74, 1999, 431-443.
D. Ouinas, A.hebbar and J.Vina, Fracture mechanics modelling of cracked aluminium panel repaired with bonded composite circular patch, Journal of Applied Science. 6 (9) pp 2088-2096, 2006.
D. Ouinas, B. Serier and B. B. Bouiadjra, Computation of the stress intensity factors for repaired cracks at notch with bonded composite semi-circular patch in mode I and mixed mode., 4th International Forum on Advanced Material Science and Technology, Troyes, France, 2004.
D.Ouinas, B.Serier, B.B.Bouiadjra, The Effects of Disbonds on the pure mode II Stress Intensity Factor of Aluminium Plate reinforced with bonded Composite Materials. Computational materials sciences (doi:10.1016/j.commatsci.2006.09.006 In press.
D.Ouinas, B.B.Bouiadjra and B.Serier., The effects of disbond on the stress intensity factor of aluminium panels repaired using composite materials. Journal of Composite structures (In press 2005
FRANC2D/L., A crack propagation simulator for plane layered structures. Version 1.4 User–guide, 1998.
Henshel RD, Shaw KG. Crack tip finite elements are unnecessary. Int J. Numer Meth Eng 1975;9: 495–507.
RNL. Smith, The solution of mixed-mode fracture problems using the boundary element method. Eng Anal : 5:75-80, 1988.
Ouinas D, Serier B, Bachir Bouiadjra B. Analysis of cracked aluminium plate repaired with bonded composite circular patch. In: 1st IC-EpsMsO, international conference organized in Athens-Greece 2005.
D.Ouinas, B.B.Bouiadjra, B.Serier and M.Belhouari, Analysis of cracked aluminium plate repaired with bonded composite octagonal patch. In: International Conference and technology, American University on SHARJAH, 15 May 2005
D.Ouinas, B.Serier and B.B.Bouiadjra. Calcul numérique des paramètres de rupture d’une plaque fissurée renforcée par un patch métallique circulaire en mode I et mode mixte. Revue des composites et des matériaux avancés. Vol 13. n°2/2003.
Baker AA, Callinan RJ, Davis MJ, Jones R, Williams JG. Repair of mirage III aircraft using BERP crack patching technology. Theor Appl Fract Mech 1984;2:1–16.
Baker AA. Repair of cracked or defective metallic components with advanced fiber composites an overview of Australian work. Composite Structures 1984;2:153–81.
Baker AA. Bonded composite repair for fatigue cracked primary aircraft structure. Composite Structures 1999;74:431–43.
D. Ouinas, B. Serier et B. B. Bouiadjra., Calcul numérique des paramètres de rupture d'une plaque fissurée renforcée par un patch circulaire. 4èmes journées de Mécanique, Algérie, EMP, 2004.
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