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Composite materials are widely used in aircraft structures, their relative rigidity/weight confers their advantage over metal structures, and the stacking sequence plays an important role for their use. The objective of this work is to analyze by the finite element method the mechanical behavior of a single lap joint of composite/composite type under a tensile load. In order to see the effects on the failure load, two basic parameters are taken into consideration; the stacking sequence of composite and thickness of each layer constituting the composite. Calculation of the failure load is made numerically with the ABAQUS code using the developed technique of VCCT (Virtual Crack Closure Technique) based on fracture mechanics. Finally, the influence of the bonding defect on the failure load is analyzed. The results clearly show the importance of optimizing fiber orientation and hence the stacking sequence for proper use of composite in bonded assemblies.
Czasopismo
Rocznik
Tom
Strony
1257--1268
Opis fizyczny
Bibliogr. 25 poz., rys., tab.
Twórcy
autor
- Laboratoire de la Recherche en Technologie de Fabrication M´ecanique, Ecole Nationale Polytechnique of Oran, Oran, Algeria
autor
- Laboratoire M´ecanique Physique des Mat´eriaux (LMPM), University of Sidi Bel Abbes, Sidi Bel Abbes, Algeria
autor
- Laboratoire de Biom´ecanique Appliqu´ee et de Biomat´eriaux, Ecole Nationale Polytechnique of Oran, Oran, Algeria
autor
- Laboratoire des Sciences de l’Ing´enieur pour l’Environnement, Universit´e de La Rochelle, La Rochelle, Cedex, France
Bibliografia
- 1. Adams R., Atkins R., Harris J., Kinloch A., 1986, Stress analysis and failure properties of carbon-fibre reinforced plastic/steel double lap-joint, Journal of Ahdesives, 20, 29-30
- 2. Adkins D.W., Pipes R.B., 1988, Tensile behaviour of bonded scarf joints between composite adherend, Proceedings of the Fourth Japan – US Conference on Composite Materials, 845-854
- 3. Ahn J.S., Woo K.S., 2015, Delamination of laminated composite plates by p-convergent partial discrete-layer elements with VCCT, Mechanics Research Communications, 66, June, 60-69
- 4. Benchiha A., Madani K., 2015, Influence of the presence of defects on the stresses shear distribution in the adhesive layer for the single-lap bonded joint, Structural Engineering and Mechanics, 53, 5, 1017-1030
- 5. Campilho R., de Moura M.F.S.F, Domingues J.J.M.S., 2005, Modelling single and doublelap repairs on composite materials, Composites Science and Technology, 65, 1948
- 6. De Moura M.F.S.F., Daniaud R., Magalhaes A.G. , 2006, Simulation of mechanical behaviour of composite bonded joints containing strip defects, International Journal of Adhesion and Adhesives, 26, 464-473
- 7. Irwin G.R., 1958, Fracture, [In:] Handbuch der Physik, Flugge S., (Ed.), vol. VI, Springer, Berlin, 551-590
- 8. Janssen M., Zuidema J., Wanhill R.J.H., 2004, Fracture Mechanics, Spon Press Taylor & Francis, ISBN 0415346223
- 9. Jokinen J., Wallin M., Saarela O., 2015, Applicability of VCCT in mode I loading of yielding adhesively bonded joints - a case study, International Journal of Adhesion and Adhesives, 62, October, 85-91
- 10. Karachalios E.F., Adams R.D., da Silva L.F.M., 2013, Strength of single lap joints with artificial defects, International Journal of Adhesion and Adhesives, 45, 69-76
- 11. Klug J., Wu X., Sun C.T., 1996, Efficient modeling of postbuckling delamination growth in composite laminates using plate elements, AIAA Journal, 34, 178-184
- 12. Krueger R., 2004, The virtual crack closure technique: history, approach and applications, Applied Mechanics Reviews, 57, 2, 109-143
- 13. Kumar S.B., Sridhar I., Sivashanker S., Osiyemi S.O., Bag A., 2006, Tensile failure of adhesively bonded CFRP composite scarf joints, Materials Science and Engineering B, 132, 113-120
- 14. Liu L., Zhang J., Wang H., Guan Z., 2015, Mechanical behavior of the composite curved laminates in practical applications, Steel and Composite Structures, 19, 5
- 15. Mokhtari M., Madani K., Belhouari M., Touzain S., Feaugas X., Ratwani M., 2013, Effects of composite adherent properties on stresses in double lap bonded joints, International Journal of Mechanics and Materials in Design, 44, 633-639
- 16. Mukherjee Y.X., Gulrajani S.N., Mukherjee S., Netravali A.N., 1994, A numerical and experimental study of delaminated layered composites, Applied Mechanics Reviews, 28, 837-870
- 17. Ray C., Majamuder S., 2014, Failure analysis of composite plates under static and dynamic loading, Structural Engineering and Mechanics, 52, 1
- 18. Rybicki E.F., Kanninen M.F., 1977, A finite element calculation of stress intensity factors by a modified crack closure integral, Engineering Fracture Mechanics, 9, 931-938
- 19. Shiming C., Xiaoyu S., Zihao Q., 2011, Shear bond failure in composite slabs – a detailed experimental study, Steel and Composite Structures, 11, 3
- 20. Shishesaz M., Bavi N., 2013, Shear stress distribution in adhesive layers of a double-lap joint with void or bond separation, Journal of Adhesion Science and Technology, 27, 11, 1197-1225
- 21. Shivakumar K.N., Tan P.W., Newman J.C., 1988, A virtual crack-closure technique for calculating stress intensity factors for cracked three dimensional bodies, International Journal of Fracture, 36, R43-R50
- 22. Shokrieh M.M., Rajabpour-Shirazi H., Heidari-Rarani M., Haghpanahi M., 2012, Simulation of mode I delamination propagation in multidirectional composites with R-curve effects using VCCT method, Computational Materials Science, 65, December, 66-73
- 23. Tsai M., Morton J., Matthews F., 1995, Experimental and numerical studies of a laminated composite single-lap adhesive joint, Journal of Composite Materials, 29, 1254-1275
- 24. Varughese B., Mukherjee A., 1997, Ply drop-off in layered composites-evaluation of design parameters, [In:] Computational Structural Mechanics, Allied Publishers Ltd., 473-482
- 25. Whitcomb J.D., 1989, Three-dimensional analysis of a postbuckled embedded delamination, Journal of Composite Materials, 23, 862-889
Typ dokumentu
Bibliografia
Identyfikator YADDA
bwmeta1.element.baztech-562a9967-ab22-4d83-9769-6714f356e60c