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| Naji, M. |
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| Motta, Antonella |
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| Aletan, Dirar |
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| Mohamed, Tarek |
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| Ertürk, Emre |
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| Taccardi, Nicola |
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| Kononenko, Denys |
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| Petrov, R. H. | Madrid |
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| Alshaaer, Mazen | Brussels |
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| Bih, L. |
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| Casati, R. |
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| Muller, Hermance |
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| Kočí, Jan | Prague |
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| Šuljagić, Marija |
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| Kalteremidou, Kalliopi-Artemi | Brussels |
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| Azam, Siraj |
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| Ospanova, Alyiya |
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| Blanpain, Bart |
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| Ali, M. A. |
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| Popa, V. |
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| Rančić, M. |
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| Ollier, Nadège |
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| Azevedo, Nuno Monteiro |
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| Landes, Michael |
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| Rignanese, Gian-Marco |
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Gurdal, Z.
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Topics
Publications (9/9 displayed)
- 2014Fibre steering for shear-loaded composite panels with cutoutscitations
- 2012In-plane stiffness tailoring for the improvement of buckling and strength of composite panels with cut-outs
- 2010Tailoring for strength of steered-fibre composite panels with cutouts
- 2010Tailoring for strength of composite steered-fibre panels with cutoutscitations
- 2010Damage tolerance of non-conventional laminates with dispersed stacking sequences
- 2009Low-velocity impact damage on dispersed stacking sequence laminates. Part I: Experimentscitations
- 2009Low-velocity impact damage on dispersed stacking sequence laminates. Part II: Numerical simulationscitations
- 2008Variable-stiffness composite panels: Buckling and first-ply failure improvements over straight-fibre laminatescitations
- 2007Progressive failure analysis of tow-placed, variable-stiffness composite panels
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article
Variable-stiffness composite panels: Buckling and first-ply failure improvements over straight-fibre laminates
Abstract
One of the primary advantages of using fibre-reinforced laminated composites in structural design is the ability to change the stiffness and strength properties of the laminate by designing the laminate stacking sequence in order to improve its performance. This procedure is typically referred to as laminate tailoring. Traditionally, tailoring is done by keeping the fibre orientation angle within each layer constant throughout a structural component. Allowing the fibres to follow curvilinear paths within the plane of the laminates constitutes all advanced tailoring option that can lead to modification of load paths within the laminate to result in more favourable stress distributions and improve the laminate performance. Based on numerical simulations, the present work demonstrates the advantages of variable-stiffness over straight-fibre laminates in terms of compressive buckling and first-ply failure. A physically based set of failure criteria, able to predict the various modes of failure of a composite laminated structure, is implemented in finite element models of straight and variable-stiffness panels under compression. Non-linear analyses are carried out to simulate first-ply failure in the postbuckling regime.