| 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
Discrete Stiffness Tailoring for Improved Buckling Performance
Abstract
Continuously varying fibre angle across flat plates has analytically been shown to improve buckling performance by up to 60%. However, manufacture of such panels has so far used methods which have either high radius of curvature and low deposition rate (Continuous Tow Shearing) or low radius of curvature and medium deposition rate (Advanced Fibre Placement). Discrete Stiffness Tailoring (DST) is an alternative way of varying fibre angle to increase buckling performance that is compatible with current high rate deposition methods such as Advanced Tape Laying (ATL). DST uses discrete changes of angle within individual layers to effect variation in stiffness across a composite component at the cost of in-plane butt joints within layers. Two schemes of distribution are considered for tailoring stiffness across the width of a panel; (i) Half Seam; where half the layers in a laminate are subject to tailoring and (ii) Full Seam; where all layers are tailored. Compression testing of flat panels shows that DST can improve buckling stress for Full Seam by up to 16% for the simple example of redistributing material in a standard angle quasi-isotropic [±45/90/0]<sub>2S</sub> laminate. Comparison of experimental results with standard buckling analyses (FEA, VICONOPT) indicates that DST results are predictable within the bounds of error introduced by experimental boundary conditions. Although no compression strength reductions were apparent in compression testing, tensile testing of seamed regions shows that improved buckling performance comes at the cost of reductions in transverse strength for Half Seam and Full Seam schemes. However, such reductions should be acceptable where loading is compression dominated and seams run parallel to the load.