Trans RINA, Vol 152, Part B2, Intl J Small Craft Tech, 2010 Jul-Dec


As the specimen was not loaded by pure moment, the failure does not occur at 450. FEA results of layups 1 and 2 were comparable to the experimental data. FEA prediction for


layup 3 was not comparable with the


experimental results as the residual strength could not be modelled. The maximum interlaminar shear stress for all


the three layups occurred at the lower end of the laminate bend. The failure criterion for the finite element analysis is a function of both the interlaminar tensile and shear stresses. Hence failure initiated near the bottom curvature as shown in Figures 6.1 & 6.3.


Figure 6.1: Interlaminar tensile stress distribution – all three layups


Figure 6.2: Interlaminar Tensile Stress distribution just before first failure – all three layups [34]


Figure 6.3: Interlaminar shear stress distribution- all three layups


Figure 6.4: Interlaminar Shear Stress distribution just before first failure – all three layups ©2010: The Royal Institution of Naval Architects B-103


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