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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
Tailoring for strength of steered-fibre composite panels with cutouts
Abstract
The traditional approach to the problem of stress concentrations around cutouts in composite structures is to locally increase the laminate thickness in order to smooth out the stress peak. Often, this practice attracts more loads to the cutout region besides increasing part weight. A more effective solution is to avoid the stress concentrations altogether by using fibre-steered laminates. The production of composites in this format is practical nowadays due to capabilities of advanced fibre-placement technology. This paper shows that it is possible to design and manufacture composite panels whose failure responses is insensitive to the existence of a central hole. This cutout insensitivity does not involve an increase in structural mass, but only the steering of the fibres in the plane of the laminate, in order to promote the redistribution of the loading towards the supported edge sections of the panel. Copyright © 2010 by the American Institute of Aeronautics and Astronautics, Inc.