PSI - Issue 60
Amardeepa KCS et al. / Procedia Structural Integrity 60 (2024) 60–74 Amardeepa KCS/ StructuralIntegrity Procedia 00 (2023) 000–000
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the point of application of enforced displacement (D1 and D2), values are the same as that of applied enforced displacement called in Table 1. The variation in the maximum displacement values was found to be only 4-5% when compared with that of a global wing (component), wing box (sub-component), and standalone L angle. The 2D layers are connected by 1D CBAR elements at zone 2 Figure 10(e) & Figure 11(b) with a rectangular cross-section property adopted for modelling by choice.
Fig. 17. Axial force for 1 st row of elements
Fig. 18. Shear force in Plane 1 for 1 st row of elements
Fig. 19. Shear force in Plane 2 for 1 st row of elements
Fig. 20. Max displacement along z
A 3D view of the 1D CBAR elements is shown in Figure 21(a)&(b) for zones 2,3 and 4. The Normal Stress (σ n ) at zone 2,3, and 4 are plotted by choosing the CBAR elements in the clockwise direction, as shown in Figure 21(a). There are 16 elements along the column and 25 elements in the row, and 4 points (P1, P2, P3, and P4) at each layer (layer 1 to Layer 4) shown in Figure 10(a) across the thickness direction in the curved region. The points are chosen along the column (22-41) in row 1 (153-172) in row 2, and so on up to row 25, as shown in Figure 16(b) and Figure 21(a). The normal stress distribution is plotted in Figure 22 at zone 2 for all 25 rows. The out-of-plane stress value that induces the tensile stress between each layer is 13.25 MPa at zone 2 and 20.90 MPa at zone 3 and 4, which is less than 53 MPa (the resin tensile strength or transverse tensile strength property of the composite laminate). The resultant shear stress due to Plane 1& 2 is 11.10 MPa, and axial stress for zone 2 is 7.92 MPa, plotted for one case (max displacement 0.7), as shown in Figure 23 & 24, respectively.
(a) 3D view of CBAR elements at zone 2
(b) 3D view of CBAR elements at Zone 3 and 4
Fig. 21. 3D view of 1D CBAR elements
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