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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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Toftegaard, Helmuth Langmaack
Technical University of Denmark
in Cooperation with on an Cooperation-Score of 37%
Topics
Publications (10/10 displayed)
- 2023J integral strain-curvature approach for multilayer fracture specimens with unknown thickness and stiffness of layerscitations
- 2018Preface for the 39th Risø Symposium Proceedings, IOP publication
- 2018Proceedings of the 39th Risø International Symposium
- 2017Fatigue crack growth in mode II of adhesively joined composites
- 2016Delamination initiated by a defect
- 2014Experimental and theoretical assessment of flexural properties of hybrid natural fibre compositescitations
- 2014Effects of equal channel angular extrusion on microstructure, strength and ballistic performance of AA5754 plates
- 2014Environmental effect on the mechanical properties of commingled-yarn-based carbon fibre/polyamide 6 compositescitations
- 2014Environmental effect on the mechanical properties of commingled-yarn-based carbon fibre/polyamide 6 compositescitations
- 2009Effects of Heat-treatments on the Mechanical Strength of Coated YSZ: An Experimental Assessmentcitations
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article
Delamination initiated by a defect
Abstract
Composite materials in wind turbines are mainly joined with adhesives. Adhesive joining is preferable since it distributes the stresses over a larger area. This study shows how a defect can influence the fracture behaviour of adhesively joined composite. Repeated experiments are performed using double cantilever beam specimens loaded with bending moments. The specimens consist of two 8 mm thick GFRP-laminates which are joined by a 3 mm thick epoxy adhesive. A thin foil close to one of the laminates is used to start the crack. For some of the specimens a defect is created by an initial load-unload operation. During this operation, a clamp is used in order to prevent crack propagation in the main direction. For the specimens without defect, the crack propagates in the middle of the adhesive layer. For the specimens with defect, the crack directly deviates into the laminate. After about 25 mm propagation in the laminate, the crack returns to the adhesive. Compared to the adhesive the fracture energy for the laminate is significantly higher.