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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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Lindgaard, Esben
in Cooperation with on an Cooperation-Score of 37%
Topics
Publications (21/21 displayed)
- 2024An accurate forming model for capturing the nonlinear material behaviour of multilayered binder-stabilised fabrics and predicting fibre wrinklingcitations
- 2024That’s how the preform crumples: Wrinkle creation during forming of thick binder-stabilised stacks of non-crimp fabricscitations
- 2024MatrixCraCS: Automated tracking of matrix crack development in GFRP laminates undergoing large tensile strains
- 2024Parametric study on the effect of material properties, tool geometry, and tolerances on preform quality in wind turbine blade manufacturingcitations
- 2023Benchmark test for mode I fatigue-driven delamination in GFRP composite laminatescitations
- 2023Benchmark test for mode I fatigue-driven delamination in GFRP composite laminates: Experimental results and simulation with the inter-laminar damage model implemented in SAMCEFcitations
- 2022Simulation of Wrinkling during Forming of Binder Stabilized UD-NCF Preforms in Wind Turbine Blade Manufacturingcitations
- 2022Delamination toughening of composite laminates using weakening or toughening interlaminar patches to initiate multiple delaminationscitations
- 20213D progressive fatigue delamination model:Deliverable 5.1
- 20213D progressive fatigue delamination model
- 2021A simple MATLAB draping code for fiber-reinforced composites with application to optimization of manufacturing process parameterscitations
- 2021Transition-behaviours in fatigue-driven delamination of GFRP laminates following step changes in block amplitude loadingcitations
- 2021UPWARDS Deliverable D5.4:Report and data on the effect of fatigue loading history on damage development
- 2021A continuum damage model for composite laminatescitations
- 2019Formulation of a mixed-mode multilinear cohesive zone law in an interface finite element for modelling delamination with R-curve effectscitations
- 2019Parametric study of the effect of wrinkle features on the strength of a tapered wind turbine blade sub-structurecitations
- 2019An evaluation of mode-decomposed energy release rates for arbitrarily shaped delamination fronts using cohesive elementscitations
- 2019Experimental characterization of delamination in off-axis GFRP laminates during mode I loadingcitations
- 2017A benchmark study of simulation methods for high-cycle fatigue-driven delamination based on cohesive zone modelscitations
- 2016Post-buckling optimization of composite structures using Koiter's methodcitations
- 2015Simulation Methods for High-Cycle Fatigue-Driven Delamination using Cohesive Zone Models - Fundamental Behavior and Benchmark Studies
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article
Experimental characterization of delamination in off-axis GFRP laminates during mode I loading
Abstract
This work experimentally investigates the influence of the off-axis angle between the lamina orientation and the crack growth direction in mode I delamination of GFRP laminates having R-curve behaviour due to large scale bridging. Initial and steady-state fracture toughness are characterized for different configurations of two laminate designs using moment loaded DCB specimens. In layup design 1, the layers adjacent to the initial delamination are parallel and the off-axis angle is varied. For layup design 2, only the off-axis angle of layers adjacent on one side of the initial delamination is varied. Microscopy, fractography, and comparisons of R-curves are used as tools to classify the cracking behaviour. All off-axis configurations tested experienced crack migration from the initial crack plane. In layup design 1, a significant difference in initial fracture toughness are found as opposed to layup design 2 in which an insignificant difference in initial fracture toughness and steady-state fracture toughness, respectively, are found. The off-axis configurations of layup design 2 are associated with crack migration and intraply crack propagation. The transition from interlaminar to intraply crack propagation correlates with the location of off-axis fibers not supported by the initial delamination indicating a free edge effect of the DCB specimen.