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The current emphasis within the composite design community is gradually shifting from achieving minimum weight designs at all costs to more cost-effective and damage tolerant structural designs. A damage tolerant structure must not only be able to effectively absorb energy locally at the point of damage initiation but must also be fail-safe. A very efficient way of designing a composite fail-safe structure is to provide it with the ability to arrest a potentially catastrophic crack by increasing its fracture resistance. The fracture behaviour of composites can be quantified by measuring its toughness and it can be broadly classified into interlaminar and intralaminar fractures. Most of the work reported in the recent literature has focused on the investigation of the interlaminar behaviour of composites with a limited number of works addressing the intralaminar fracture behaviour. The measurement of intralaminar toughness requires a pre-cracked specimen and in most cases, particularly for CFRP materials. Its determination can be based on the Linear Elastic Fracture Mechanics (LEFM) approach. Different types of specimens and crack geometries are currently available in the literature to characterise the intralaminar fracture behaviour of composites under pure mode I (Cowley & Beaumont, 1997; Konstantinos et al., 2005), mode II and mixed-mode loading (Lin & Shetty, 2003), however none of them are standardised. The specimen selection depends on the material system under investigation and expected toughness values range from initiation to propagation. It is also worth mentioning that most of these specimens were originally designed for fracture in isotropic materials. The poor performance of composites in shear and compression loading, compared to tension loading in the fibre direction may lead to failure prior to crack growth. Such restrictions impose limitations on their applicability and alternative specimen designs are needed. For mode-I, the Overheight Compact Tension (OCT) specimen has the advantage of promoting a stable crack growth which eventually enables the evaluation of both initiation and propagation values for the intralaminar toughness. Jose et al. (2001) investigated the mode I intralaminar toughness of carbon/ epoxy cross-ply laminates using overheight compact tension specimens. The experimental results were compared with finite element simulations using a modified crack-closure integral method and a methodology for calculating the stress intensity factor associated with matrix cracking and fibre fracture was presented. Based on the work by Jose et al. (2001), Pinho et al. (2006a) investigated the intralaminar toughness associated with fibre breakage in tension and fibre kinking in compression in unidirectional pre-preg composites using Compact Tension (CT)

Intralaminar Fracture Toughness Characterization of Composite Laminates