Issue 50

F. Larbi Chaht et alii, Frattura ed Integrità Strutturale, 50 (2019) 331-341; DOI: 10.3221/IGF-ESIS.50.28 335 1 2 3 4 5 Plies sequences (0)s (0/-15/15/90)s (0/-30/30/90)s (0/-45/45/90)s (0/-60/60/60/90)s Table 4 : The sequences of the plies used. The different configurations of the architecture composite structures are proposed to evaluate the behavior of their damaged. First, we used a structure plate with the same thickness and natureof fiber but the thickness of the layers changes around the notch simultaneously with different other parameters and with different orientations (Figure 1). Figure 2 : The Stacking sequence of composite used. For the configuration n°1 of the laminate, the thickness of all layers is identical of each layer and equal to 0.25 mm (Fig. 1). For the configuration n°2 and n°3, the thicknesses of the several layers of the laminate are not identical; we can found two models ; when the thickness increase progressively around the notch from 0.125mm to 0.25mm going through 0.20 mm (Fig. 3), we call it configuration n°2 and when the thickness is decrease around the notch from 0.25mm to 0.125mm going through 0.20 mm (fig.3), we call it configuration n°3. Figure 3 : Detail of the mesh of each Area. In this analysis, the mesh of the structure is refined around the area of the notch in order to accurately capture the area of damage. To simulate the damage in the plate, the linear behavior of the composite was presented using S4R shell elements (zero thickness) or the thickness of the structure was introduced into the properties of the composite. The number of elements is 13428 elements. The Hashin criterion is implemented in the structure studied, and for each modification of