Damage mechanics of composite materials: II— a damaged-based notched strength model
References (23)
- et al.
Crack development in graphite epoxy cross-ply laminates under uniaxial tension
Composites Sci. Technol.
(1985) - et al.
Finite element modelling of fracture propagation in orthotropic materials
Eng. Fract. Mech.
(1987) The strength-length relationship for carbon fibres
Composites Sci. Technol.
(1987)- Kortschot, M. T. & Beaumont, P. W. R., Damage mechanics of composite materials, I—Measurements of damage and strength....
- et al.
Notched strength of composite laminates: predictions and experiments—a review
J. Reinf. Plas. Composites
(1985) - et al.
On the effect of matrix cracks on laminate strength
J. Reinf. Plas. Composites
(1987) - et al.
The extension of crack tip damage zones in fiber reinforced plastic laminates
J. Composite Mater.
(1975) The finite element method for prediction of crack behavior
Nucl. Eng. Design
(1969)- et al.
Crack tip finite elements are unnecessary
Int. J. Numer. Meth. Eng.
(1975) High resolution strain measurement by direct observation in the scanning electron microscope
J. Mater. Sci.
(1988)
Damage based notched strength modelling: a summary
Cited by (60)
On matrix cracking and splits modeling in laminated composites
2018, Composites Part A: Applied Science and ManufacturingCitation Excerpt :A comparison with experiments is also detailed. Here we refer to Kortschot and Beaumont’s experimental works on a tensile test with a large number of double-edge-notched cross-ply laminates published in a four-part series [29–32] as well as to those of the VERTEX project dedicated to validation of continuum damage models performed by Airbus Group Innovations (AGI) on open-hole laminates with more complex lay-up forms. The mesomodel for laminates aims at modeling the physics of degradation and its evolution at the ply’s scale thanks to the continuum damage mechanics.
Notch insensitive orientation-dispersed pseudo-ductile thin-ply carbon/glass hybrid laminates
2018, Composites Part A: Applied Science and ManufacturingCitation Excerpt :Due to the importance of the notched strength in the design of composite structures, considerable research has been undertaken to investigate the notched behaviour of these materials [1–5]. Many parameters such as notch size and geometry, laminate size and thickness, machining quality, ply orientation and thickness, and material constituents affect the complex failure mechanisms during the loading of notched laminates [6–14]. These parameters change the damage mechanisms during loading and have a profound effect on laminate strength and notch sensitivity.
A numerical investigation into size effects in centre-notched quasi-isotropic carbon/epoxy laminates
2015, Composites Science and TechnologyStrength prediction of bolted joints in CFRP composite laminates using cohesive zone elements
2014, Composites Part B: EngineeringDamage development in open-hole composite specimens in fatigue. Part 2: Numerical modelling
2013, Composite StructuresCitation Excerpt :In the (0/±45)2s specimens failure occurred through fibre breakage and fibre–matrix shearing. Kortschot and Beaumont [19–21] developed an FE model that explicitly meshed the shape of the damage zones in graphite/epoxy composites with a (0n/90n)ns general layup [19]. Delamination and splitting was modelled using two layers of plane stress elements with damage embedded using coincident nodes.
Damage development in open-hole composite specimens in fatigue. Part 1: Experimental investigation
2013, Composite Structures
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Present address: Department of Chemical Engineering and Applied Chemistry, University of Toronto, 200 College Street, Toronto, Canada M5S 1A4.