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| Petrov, R. H. | Madrid |
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| Bih, L. |
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| Casati, R. |
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| Azevedo, Nuno Monteiro |
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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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document
In-plane stiffness tailoring for the improvement of buckling and strength of composite panels with cut-outs
Abstract
The traditional engineering approach to the problem of stress concentrations around large cutouts in composite aerospace structures, e.g. for windows and doors in aircraft, is to locally increase the thickness in order to lower the stress peaks. Often, this practice results in a significant increase in the weight of the structure. A more effective solution, avoiding the mass increase, is to dissipate the stress concentrations by redistributing loads to supported regions, such as frames and stiffeners, by means of fibre-steered laminates with variable in-plane stiffness. The production of composites in this format is practical nowadays due to the capabilities of advanced fibre-placement technology. In this work, the potential of the fibre-steering concept for the purpose of stress alleviation around cutouts in composite laminates is explored. Numerical studies are performed on compression and shear loaded variable-stiffness panels of different configurations and hole-to-panel size ratios in order to identify the optimal configurations in terms of buckling and first-ply failure.