Issue 73

J. M. Parente, et alii, Fracture and Structural Integrity, 73 (2025) 139-152; DOI: 10.3221/IGF-ESIS.73.10

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Figure 8: Energy dissipated by intralaminar damage in each layer for: a) 7C/1G; b) 1G/7C; c) 6C/2G; d) 2G/6C; e) 5C/3G; f) 3G/5C; g) 8C; h) 8G. Bold represent laminas composed by glass fibre. The dashed lines represent the displacement at the peak force.

Figure 9: Tensile damage in hybrid laminate configurations 2G/6C and 6C/2G. As depicted in Fig. 9, the tensile damage results indicate that for the 2G/6C configuration, the damage is observed in layers #7 and #8, which correspond to the final two layers of carbon fibre behind the centre of the specimen. As the sample reaches the peak force, the damage propagates up to layer #6, at which point the sample's mechanical performance begins

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