Issue 50

F. Larbi Chaht et alii, Frattura ed Integrità Strutturale, 50 (2019) 331-341; DOI: 10.3221/IGF-ESIS.50.28 340 In figure 9, force / displacement curves for structures with modification 1 and 2 have been presented with the stacks which each have a high optimized resistance (15° and 60°). Subsequently, the thickness of the folds, which have the same fiber orientations for each case, has been reinforced as an evaluative parameter, which makes it possible to have their effects on the resistance of the structure. Note that for the two curves, the reinforcement 0° and 90° folds have significant values than other angles except those without modification. C ONCLUSION his work has demonstrated the effectiveness of a 2D numerical approach with the use of Hashin criterion of damage and with shell elements in laminated composite structures notches. It is also demonstrated the effectiveness of the reinforcement by geometric modifications that summarize our objective. • The use of the Hashin criterion gives the advantage of analyzing the damage of composite structures with complex geometries. •The geometrical propositions studied can be accompanied by several parameters that make them more useful in the resistance of notched composite structures. • The value of the failure load is influenced by the type of the load applied and impalement sequence. •The introduced changes present a change in the response of the structure to the changes. • The carbon/epoxy composite absorbs better the stress than the aramid/epoxy and therefore a reduction in the value of load is observed. •The damage value and the propagation path follow the orientation of the fibers in the stress concentration zone. • The rack birth and its propagation depend directly on the fiber orientation at of the notch tip. R EFERENCES [1] ABAQUS, Abaqus Version (2009). 6.9 Documentation. Providence, RI: Dassault Systems Simulia Corporation. [2] Bureau of Accident Investigation. (1989). Aircraft Accident Report: Aloha AirlinesFlight 243 Boeing 737-200. National Transportation and Safety Office. Available at: https://www.faa.gov/about/initiatives/maintenance_hf/library/documents/media/human_factors_maintenance/air craft_accident_report--aloha_airlines.flight_243.boeing_737-200.n73711. near_maui.hawaii.april_28. 1988. [3] Ponces Camanho, P. (2002). Failure criteria for fibre-reinforced polymercomposites, DEMEGI. [4] Lu, J., Lieurade, H P., Tehniques de l’Ingénieur, Concentration de contraintes, Génie mécanique BM 5, 40, pp. 1–24. [5] Madani, S., Touzain, X., Feaugas, S., Cohendouz, M., Ratwani, M. (2010) Experimental and numerical study of repair techniques for panelswith geometrical discontinuities. Computational Materials Science (48), pp.83–93. DOI: 10.1016/j.commatsci.2009.12.005 [6] Mokhtari, M., Madani, K., Benzaama, H., Malarino, S.(2017).Effects of the composite stacking sequence on the failure load of the single lap bonded joint. Journal of Theoretical And Applied Mechanics, 55(4), pp. 1257-1268. [7] Mokhtari,M., Madani, K., Belhouari ,M., Touzain, S., Feaugas, X., Ratwani ,M .(2013).Effects of composite adherend properties on stresses in double lap bonded joints. Materials and Design, 44, pp. 633–639. DOI: http://dx.doi.org/10.1016/j.matdes.2012.08.001. [8] Ait Kaci, D., Madani, K., Mokhtari, M., Feaugas,X. ,Touzain,S.(2017) .Impact of composite patch on the J-integralin adhesive layer for repaired aluminum plate. Advances in Aircraft and Spacecraft Science,4(6),pp. 679-699. [9] Benzaama, A., Mokhtari,M., Benzaama, H., Gouasmi, S., Tamine, T. (2018).Using XFEM technique to predict the damage of unidirectional CFRP composite notched under tensile load. Advances in Aircraft and Spacecraft Science,5(1), pp. 129-139. [10] Donadon, M. V., De Almeida, S F M., Arbelo,M A., Orúe, A B. (2009). A three-dimensional ply failure model for composite structures. International Journal of Aerospace Engineering. DOI: 10.1155/2009/486063. [11] Linde, P., De Boer, H. (2011). Behaviour of solid like shell elements in simulation of composites in aircraft structures.16th International Conference on Composite Structures ICCS 16 A. J. M. Ferreira (Editor) FEUP, Porto, Portugal. [12] Elangovan, P. (2012). A Study on Solid and Shell Material Model in Stamping Simulation. Stamping Simulation Engineer Valeo India Private LimitedBlock - A, 4th Floor, TECCI Park No. 176 Rajiv Gandhi Salai Sozhanganallur Chennai ,pp.600-119. India, HTS. T