Journal
THEORETICAL AND APPLIED FRACTURE MECHANICS
Volume 107, Issue -, Pages -Publisher
ELSEVIER
DOI: 10.1016/j.tafmec.2020.102473
Keywords
Composite laminates; Intralaminar fracture toughness; Crack resistance curves; Finite element analysis
Categories
Funding
- Airbus
- University of Dayton Research Institute (UDRI)
- Portuguese Government's Fundacao para a Ciencia e Tecnologia [SFRH/BD/115859/2016]
- FCT Fundacao para a Ciencia e Tecnologia [MITP-TB/PFM/0005/2013]
- Fundação para a Ciência e a Tecnologia [SFRH/BD/115859/2016] Funding Source: FCT
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The apparent crack resistance curves associated with longitudinal tensile failure of carbon fibre reinforced epoxy composite systems with ply thicknesses of 0.075 mm, 0.134 mm and 0.268 mm are determined experimentally from the size effect law of geometrically similar double edge notch tension cross-ply specimens. An increase in notched strength as a function of the ply thickness and a corresponding increase of the measured intralaminar fracture toughness is observed. This increase is shown to be a consequence of the appearance of split cracks in the thicker 0 degrees plies in the vicinity of the notches. The numerical models developed demonstrate that if the notch blunting mechanisms are properly represented, the laminate strength is well predicted for a constant value of the ply intralaminar fracture toughness. This supports the hypothesis that these mechanisms are responsible for the higher strength of the thicker plies, and that the intralaminar fracture toughness of the 0 degrees plies should not be scaled with the ply thickness.
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