By Jim Sullivan
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Additional resources for A-3 Skywarrior in Action No 148
2 Composite Delaminated Panels Loaded in Compression The composite panels geometrical and material configurations, used for the validation of the developed numerical tools, have been taken from  where the experimental results for cross-ply carbon fiber/epoxy laminated panels with an implanted artificial delamination are reported. 14. 14 as A, B, C, D) has been considered for the numerical simulations thanks to the conditions of symmetry with respect to the x and y axes of geometry, boundary conditions and applied loads.
The specimen is clamped at one edge and loaded in tension on the other one. 9. 10, the PDA elements have been used for discretization of the area with stress concentration (region near the hole). 10). 35 mm A. Riccio et al. 10 Mesh description—tension-loaded laminate with hole Literature results for this test case are available in [57–59] and employed to perform appropriate comparisons. The result of the B2000/PDA tool in terms of final failure load is in excellent agreement with the numerical results of Ref.
27. 27, σeq and δeq denote respectively the equivalent stress and the equivalent displacement computed for each of the four damage modes. The first part of the stress-displacement curve, prior to the damage initiation, is representative of the linear elastic material behavior; the second part with negative slope, after the damage initiation, is associated to the damage evolution. 18). 18) where GC represents the intra-laminar fracture energy and LC the characteristic length of the element. A. Riccio et al.
A-3 Skywarrior in Action No 148 by Jim Sullivan