| 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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Rhead, Andrew T.
University of Bath
in Cooperation with on an Cooperation-Score of 37%
Topics
Publications (40/40 displayed)
- 2024An analytical model for wrinkle-free forming of composite laminatescitations
- 2021Effects of ply angle and blocking on open-hole tensile strength of composite laminatescitations
- 2021Buckle-driven delamination models for laminate strength prediction and damage tolerant designcitations
- 2021A data-driven Bayesian optimisation framework for the design and stacking sequence selection of increased notched strength laminatescitations
- 2020Edge treatment of short beam shear tests for improved assessment of structural strengthcitations
- 2020Buckling and strength analysis of panels with discrete stiffness tailoringcitations
- 2019Novel filler materials for composite out-of-plane jointscitations
- 2019Stacking sequence selection for defect-free forming of uni-directional ply laminatescitations
- 2019Novel filler materials for skin-stiffener structures
- 2019Buckling and strength analysis of panels with discrete stiffness tailoringcitations
- 2018Numerical Prediction of Failure in Composite T-joints Using Progressive Damage Modellingcitations
- 2018Optimum design and damage tolerance of compressively loaded laminatescitations
- 2017Ply interface angles to promote automated forming of aerospace structures
- 2017Reshaping the testing pyramid: utilisation of data-rich NDT techniques as a Means to Develop a ‘High Fidelity’ Component and Sub-structure Testing Methodology for Composites
- 2017Discrete Stiffness Tailoring for Improved Buckling Performance
- 2017Delamination growth rate in composite laminates under increasing low-velocity impact energy
- 2017Compressive strength of composite laminates with delamination-induced interaction of panel and sublaminate buckling modescitations
- 2016Ply-By-Ply Delamination Morphology In Composite Laminates Under Low-Velocity Impact
- 2016Optimum fibre-steering of composite plates for buckling and manufacturabilitycitations
- 2015Damage resistance and damage tolerance of hybrid carbon-glass laminatescitations
- 2015X-ray computed tomography of damage formation under in-situ loading
- 2014Investigation of failure modes in impact damaged steered fibre laminates
- 2013Compression after impact strength of a buckling resistant tow steered panel
- 2013Optimized fiber steering and layer stacking for elastically tailored, damage tolerant laminates
- 2013Compression after impact strength of a buckling resistant, tow steered panel
- 2013The effect of tow gaps on compression after impact strength of robotically laminated structures
- 2012Compressive strength following delamination induced interaction of panel and sublaminate bucklingcitations
- 2012The effect of tow gaps on compression after impact strength of AFP laminates
- 2012The influence of surface ply fibre angle on the compressive strength of composite laminates containing delamination
- 2012Compressive strength of delaminated aerospace compositescitations
- 2011Damage resistance and damage tolerance of hybrid carbon-glass laminates
- 2011Damage Resistance and Damage Tolerance of Hybrid Carbon-Glass Laminates
- 2011Analysis and compression testing of laminates optimised for damage tolerancecitations
- 2010Buckling, propagation and stability of delaminated anisotropic layers
- 2010Compressive strength of composite laminates following free edge impactcitations
- 2009Post-buckled propagation model for compressive fatigue of impact damaged laminatescitations
- 2009Compressive static strength model for impact damaged laminatescitations
- 2009Compression Testing of Laminates Optimised for Damage Tolerance
- 2008A static compressive strength model for damaged composite laminates
- 2007Enhanced compressive fatigue model for impact damaged laminates
Places of action
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document
Ply interface angles to promote automated forming of aerospace structures
Abstract
The success of an automated vacuum forming process where flat prepreg laminates are formed into parts with complex curvature, is heavily influenced by the capacity of plies to deform during the forming procedure. Understanding the deformation behaviour in single and multi-layer prepreg arrangements gives insight into the likelihood of defect generation and the possible solutions which lead to defect free parts. The paper presents a theoretical model based on eigenvector and eigenvalue analysis to determine compatible modes of deformation within individual ply interfaces and complete stacking sequences. The model is validated using an experimental process where laminates are formed onto a doubly curved tool geometry using an industrial double diaphragm former. Stacking sequences with 90° interface angles outline the most formable solutions, whereas continuous 45° interfaces that spiral e.g. 45/0/-45/90 outline the most problematic forming conditions due to a locking behaviour. Optimising the interface angle within a stack for maximum compatibility is shown to completely remove defects at elevated temperature. Interface angles and stacking sequence are thus seen to be as significant as temperature and vacuum rate on the quality of formed parts.