| People | Locations | Statistics |
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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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Kawashita, Luiz F.
University of Bristol
in Cooperation with on an Cooperation-Score of 37%
Topics
Publications (24/24 displayed)
- 2023Efficient sublaminate-scale impact damage modelling with higher-order elements in explicit integrationcitations
- 2023Manufacturing composite laminates with controlled void content through process controlcitations
- 2022Predicting interlaminar damage behaviour of fibre-metal laminates containing adhesive joints under bending loadscitations
- 2022Mesh independent modelling of tensile failure in laminates using mixed-time integration in explicit analysiscitations
- 2021Modelling delaminations using adaptive cohesive segments with rotations in dynamic explicit analysiscitations
- 2021Compaction behaviour of continuous fibre-reinforced thermoplastic composites under rapid processing conditionscitations
- 2020Damage sequence of honeycomb sandwich panels under bending loading:Experimental and numerical investigationcitations
- 2020Effect of processing parameters on quality and strength in thermoplastic composite injection overmoulded components
- 2020Analysis of novel hybrid joints for composite struts
- 2020Composites fatigue delamination prediction using double load envelopes and twin cohesive modelscitations
- 2020An experimental and numerical investigation into damage mechanisms in tapered laminates under tensile loadingcitations
- 2018Electrical and Thermal Effects of Fault Currents in Aircraft Electrical Power Systems With Composite Aerostructurescitations
- 2018Electrical and Thermal Effects of Fault Currents in Aircraft Electrical Power Systems with Composite Aerostructurescitations
- 2017Understanding the effect of void morphology and characteristics on laminate mechanical properties
- 2017Void modelling and virtual testing of prepreg materials from 3D image capture
- 2016Effect of voids on interlaminar behaviour of carbon/epoxy composites
- 2015Experimental and numerical analysis of peel failure between alumina ceramics and glass fibre-reinforced composites
- 2013Analysis of Delamination Migration in Laminated Composited using Conventional and Mesh-Independent Cohesive Zone Models
- 2013Modeling of Delamination Migration in DCB test on Multidirectional Composite Laminates
- 2012A crack tip tracking algorithm for cohesive interface element analysis of fatigue delamination propagation in composite materialscitations
- 2012Modelling mesh independent transverse cracks in laminated composites with a simplified cohesive segment method
- 2011Testing and modelling of a severely tapered composites specimen
- 2010A cut ply specimen for the determination of mixed-mode interlaminar fracture toughness
- 2009Cohesive Zone Implementations for Modelling Delamination from Discontinuous Plies – Static and Fatigue Considerations
Places of action
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article
Composites fatigue delamination prediction using double load envelopes and twin cohesive models
Abstract
This paper presents an explicit finite element methodology for predicting fatigue delamination in composite laminates using twin cohesive models and a combined static & fatigue cohesive formulation; one model is loaded under the peak-load envelope, whilst the other model is loaded under the trough-load envelope. The twin models contain pairs of twin cohesive interface elements that predict delamination growth by exchanging data at every time increment. The cohesive formulation evaluates fracture mechanics parameters, e.g. the local minimum to maximum fracture energy ratio via local information associated with the twin cohesive elements, without the need to know the global loading information, e.g. the global R ratio. The method allows predicting the mechanical condition of a laminate at both the peak and trough loads. This method is validated by multiple test cases with varying mode mixities and R ratios, showing a high computation efficiency.