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7 results on '"Clément Minot"'

1. Influence of internally dropped-off plies on the impact damage of asymmetrically tapered laminated CFRP

Author

Hakim Abdulhamid, Laurent Michel, Christophe Bouvet, Jacky Aboissière, Clément Minot, Ecole nationale supérieure des Mines d'Albi-Carmaux - IMT Mines Albi (FRANCE), Institut National des Sciences Appliquées de Toulouse - INSA (FRANCE), Institut Supérieur de l'Aéronautique et de l'Espace - ISAE-SUPAERO (FRANCE), Sogeti (FRANCE), Université Toulouse III - Paul Sabatier - UT3 (FRANCE), Institut Clément Ader (ICA), Institut Supérieur de l'Aéronautique et de l'Espace (ISAE-SUPAERO)-Institut National des Sciences Appliquées - Toulouse (INSA Toulouse), Institut National des Sciences Appliquées (INSA)-Université de Toulouse (UT)-Institut National des Sciences Appliquées (INSA)-Université de Toulouse (UT)-Université Toulouse III - Paul Sabatier (UT3), Université de Toulouse (UT)-Centre National de la Recherche Scientifique (CNRS)-IMT École nationale supérieure des Mines d'Albi-Carmaux (IMT Mines Albi), Institut Mines-Télécom [Paris] (IMT)-Institut Mines-Télécom [Paris] (IMT), Institut National des Sciences Appliquées - Toulouse (INSA Toulouse), Institut National des Sciences Appliquées (INSA)-Institut National des Sciences Appliquées (INSA)-Centre National de la Recherche Scientifique (CNRS)-Université Toulouse III - Paul Sabatier (UT3), Université Fédérale Toulouse Midi-Pyrénées-Université Fédérale Toulouse Midi-Pyrénées-IMT École nationale supérieure des Mines d'Albi-Carmaux (IMT Mines Albi), and Institut Mines-Télécom [Paris] (IMT)-Institut Mines-Télécom [Paris] (IMT)-Institut Supérieur de l'Aéronautique et de l'Espace (ISAE-SUPAERO)

Subjects
Ply drop-off, Materials science, business.industry, Carbon fibers, Tapering, Epoxy, Structural engineering, Structural difference, Carbon fibre, Discontinuity (geotechnical engineering), Damage mechanics, Mechanics of Materials, visual_art, [SPI.MECA.MEMA]Engineering Sciences [physics]/Mechanics [physics.med-ph]/Mechanics of materials [physics.class-ph], Ceramics and Composites, visual_art.visual_art_medium, Mécanique des matériaux, Composite material, business, Impact behaviour
Abstract

International audience; This paper presents an experimental study of low velocity impact response of carbon/epoxy asymmetrically tapered laminates. The tests are realised at energy between 10 and 30 J on two types of layup with multiple terminated plies. The type and localisation of damage are analysed using C-scan and micrographs. Then, the data is compared with the response of corresponding respective plain laminate.The effects of some tapering parameters (taper angle, drop-off disposition and configuration) on the impact damage mechanisms are also investigated. Very similar impact damage phenomena are found between tapered and plain laminates. The presence of material discontinuity due to the resin pocket affects less the damage mechanism than the structural difference between the thick and the thin sections.

Published
2015
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2. Edge impact damage scenario on stiffened composite structure

Author

Jacky Aboissière, Christophe Bouvet, Frédéric Lachaud, Clément Minot, Benjamin Ostré, Institut Clément Ader (ICA), Institut National des Sciences Appliquées - Toulouse (INSA Toulouse), Institut National des Sciences Appliquées (INSA)-Institut National des Sciences Appliquées (INSA)-Centre National de la Recherche Scientifique (CNRS)-Université Toulouse III - Paul Sabatier (UT3), Université Fédérale Toulouse Midi-Pyrénées-Université Fédérale Toulouse Midi-Pyrénées-IMT École nationale supérieure des Mines d'Albi-Carmaux (IMT Mines Albi), Institut Mines-Télécom [Paris] (IMT)-Institut Mines-Télécom [Paris] (IMT)-Institut Supérieur de l'Aéronautique et de l'Espace (ISAE-SUPAERO), Sogeti (FRANCE), Institut Supérieur de l'Aéronautique et de l'Espace (ISAE-SUPAERO)-Institut National des Sciences Appliquées - Toulouse (INSA Toulouse), Institut National des Sciences Appliquées (INSA)-Université de Toulouse (UT)-Institut National des Sciences Appliquées (INSA)-Université de Toulouse (UT)-Université Toulouse III - Paul Sabatier (UT3), Université de Toulouse (UT)-Centre National de la Recherche Scientifique (CNRS)-IMT École nationale supérieure des Mines d'Albi-Carmaux (IMT Mines Albi), Institut Mines-Télécom [Paris] (IMT)-Institut Mines-Télécom [Paris] (IMT), Ecole nationale supérieure des Mines d'Albi-Carmaux - IMT Mines Albi (FRANCE), Institut National des Sciences Appliquées de Toulouse - INSA (FRANCE), Institut Supérieur de l'Aéronautique et de l'Espace - ISAE-SUPAERO (FRANCE), Université Toulouse III - Paul Sabatier - UT3 (FRANCE), and Département de Mécanique des Structures et Matériaux - DMSM (Toulouse, France)

Subjects
Materials science, Impact behavior, Matériaux, 02 engineering and technology, Edge (geometry), Residual, [SPI.MAT]Engineering Sciences [physics]/Materials, Analytical modeling, Damage mechanics, 0203 mechanical engineering, Carbon Fiber, Indentation, Materials Chemistry, medicine, Fiber, Composite material, business.industry, Mechanical Engineering, Stiffness, Structural engineering, Fibre-reinforced plastic, 021001 nanoscience & nanotechnology, Compression (physics), 020303 mechanical engineering & transports, Mechanics of Materials, Ceramics and Composites, medicine.symptom, 0210 nano-technology, business
Abstract

International audience; Low velocity / low energy edge impact and almost-static experiments have been carried out on carbon fiber reinforced plastic (CFRP) structures. A drop-weight testing machine was used to impact four different UD laminates at 10, 20 and 35 J impact energy levels. In parallel, an almoststatic study has been conducted in order to compare its results with the impact one. Compression after impact tests will supply the residual behavior afterwards. The impact results show that the static and dynamic behaviors are different. A simplified analytical impact model is provided trying to explain the difference between static and dynamic edge impact regardless the stacking or impact energy. It actually well represents the dynamic and static initial stiffness and the crushing plateau. The fiber properties control the initial impact stiffness. In addition, regardless of the impact energy and stacking, a specific "crushing plateau" phenomenon appears. In the almost-static indentation case the properties of the matrix control the initial indentation stiffness. The experimental results will be compared to a numerical model in order to simulate the impact and compression after impact damage.

Published
2014
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3. Finite Element analysis of CFRP laminates subjected to compression after edge impact

Author

Jacky Aboissière, Christophe Bouvet, Benjamin Ostré, Clément Minot, Institut Clément Ader (ICA), Institut National des Sciences Appliquées - Toulouse (INSA Toulouse), Institut National des Sciences Appliquées (INSA)-Institut National des Sciences Appliquées (INSA)-Centre National de la Recherche Scientifique (CNRS)-Université Toulouse III - Paul Sabatier (UT3), Université Fédérale Toulouse Midi-Pyrénées-Université Fédérale Toulouse Midi-Pyrénées-IMT École nationale supérieure des Mines d'Albi-Carmaux (IMT Mines Albi), Institut Mines-Télécom [Paris] (IMT)-Institut Mines-Télécom [Paris] (IMT)-Institut Supérieur de l'Aéronautique et de l'Espace (ISAE-SUPAERO), Sogeti (FRANCE), Centre National de la Recherche Scientifique - CNRS (FRANCE), Ecole nationale supérieure des Mines d'Albi-Carmaux - IMT Mines Albi (FRANCE), Institut National des Sciences Appliquées de Toulouse - INSA (FRANCE), Institut Supérieur de l'Aéronautique et de l'Espace - ISAE-SUPAERO (FRANCE), Université Toulouse III - Paul Sabatier - UT3 (FRANCE), Institut Supérieur de l'Aéronautique et de l'Espace (ISAE-SUPAERO)-Institut National des Sciences Appliquées - Toulouse (INSA Toulouse), Institut National des Sciences Appliquées (INSA)-Université de Toulouse (UT)-Institut National des Sciences Appliquées (INSA)-Université de Toulouse (UT)-Université Toulouse III - Paul Sabatier (UT3), Université de Toulouse (UT)-Centre National de la Recherche Scientifique (CNRS)-IMT École nationale supérieure des Mines d'Albi-Carmaux (IMT Mines Albi), and Institut Mines-Télécom [Paris] (IMT)-Institut Mines-Télécom [Paris] (IMT)

Subjects
[SPI.OTHER]Engineering Sciences [physics]/Other, Materials science, 02 engineering and technology, Edge (geometry), Residual, Autre, 0203 mechanical engineering, Compression after impact, Civil and Structural Engineering, business.industry, Delamination, Structural engineering, 021001 nanoscience & nanotechnology, Compression (physics), Finite element method, Residual strength, 020303 mechanical engineering & transports, Compressive strength, Impact, Impact damage tolerance, Ceramics and Composites, 0210 nano-technology, business, Damage tolerance, Finite element model
Abstract

International audience; Composite structures are particularly vulnerable to impact which lowers drastically theirs residualstrength. In particular, the edge impact on composite stiffener is known as a critical factor on the loss of residual compression strength. Then it is necessary to develop a model able to simulate impact and compression after impact in order to numerically optimize composite structures within impact damage tolerance. In the present paper, a unique model, based on Discrete Ply Model, allows to simulate edge impact and compression after impact (CAEI) of two stacking sequences highly oriented, representative of a real aeronautical stiffener structure. A relatively good correlation is found between experiment and model regarding the important number of phenomena which is taken into account: permanent indentation after impact, force–displacement impact curve, crack length after impact, delamination after impact, stressdisplacement CAEI curve, stress-out-of-plane displacement curve, CAEI final failure. Moreover only 14 parameters are needed to feed this model, and all are obtained using standard tests and have physical relevance. This concept is important because it allows considering running similar tests with other materials without performing complex and special identification tests but only using physical parameters of standard tests. The good results of this approach could allow to define a new design method to improve the edge impact damage tolerance.

Published
2016
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4. Numerical simulation of impact and compression after impact ofasymmetrically tapered laminated CFRP

Author

Jacky Aboissière, Christophe Bouvet, Clément Minot, Laurent Michel, Hakim Abdulhamid, Institut Clément Ader (ICA), Institut National des Sciences Appliquées - Toulouse (INSA Toulouse), Institut National des Sciences Appliquées (INSA)-Institut National des Sciences Appliquées (INSA)-Centre National de la Recherche Scientifique (CNRS)-Université Toulouse III - Paul Sabatier (UT3), Université Fédérale Toulouse Midi-Pyrénées-Université Fédérale Toulouse Midi-Pyrénées-IMT École nationale supérieure des Mines d'Albi-Carmaux (IMT Mines Albi), Institut Mines-Télécom [Paris] (IMT)-Institut Mines-Télécom [Paris] (IMT)-Institut Supérieur de l'Aéronautique et de l'Espace (ISAE-SUPAERO), Sogeti (FRANCE), Centre National de la Recherche Scientifique - CNRS (FRANCE), Ecole nationale supérieure des Mines d'Albi-Carmaux - IMT Mines Albi (FRANCE), Institut National des Sciences Appliquées de Toulouse - INSA (FRANCE), Institut Supérieur de l'Aéronautique et de l'Espace - ISAE-SUPAERO (FRANCE), Université Toulouse III - Paul Sabatier - UT3 (FRANCE), Institut Supérieur de l'Aéronautique et de l'Espace (ISAE-SUPAERO)-Institut National des Sciences Appliquées - Toulouse (INSA Toulouse), Institut National des Sciences Appliquées (INSA)-Université de Toulouse (UT)-Institut National des Sciences Appliquées (INSA)-Université de Toulouse (UT)-Université Toulouse III - Paul Sabatier (UT3), Université de Toulouse (UT)-Centre National de la Recherche Scientifique (CNRS)-IMT École nationale supérieure des Mines d'Albi-Carmaux (IMT Mines Albi), and Institut Mines-Télécom [Paris] (IMT)-Institut Mines-Télécom [Paris] (IMT)

Subjects
Ply drop-off, Materials science, Matériaux, Composite number, Aerospace Engineering, Ocean Engineering, Composite, 02 engineering and technology, Classification of discontinuities, [SPI.MAT]Engineering Sciences [physics]/Materials, 0203 mechanical engineering, Compression after impact, Composite material, Safety, Risk, Reliability and Quality, Civil and Structural Engineering, Computer simulation, business.industry, Mechanical Engineering, Delamination, Structural engineering, 021001 nanoscience & nanotechnology, Compression (physics), Residual strength, Stress field, 020303 mechanical engineering & transports, Impact, Mechanics of Materials, Automotive Engineering, Displacement field, 0210 nano-technology, business, Finite element simulation
Abstract

International audience; This paper presents a numerical simulation of impact and compression after impact (CAI) of a tapered composite laminate using a discrete ply model. Three types of damage: matrix cracking, delamination and fiber rupture are considered in the model. The presence of ply drop-off generates some discontinuities in the stress field and therefore adds difficulties to the simulation. Analyses of numerical results are performed to understand the damage and failure mechanisms in both tests. Numerical results in terms of force-displacement curves, delamination shape, CAI displacement field and residual strength are compared with experimental data. Impact simulation is in good correlation with the tests. CAI strength is under predicted and depends on quality of the meshing of the transition region. This study highlights the importance of modeling intra-ply matrix cracking for impact simulation.

Published
2016
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5. Experimental study of compression after impact of asymmetrically tapered composite laminate

Author

Clément Minot, Christophe Bouvet, Laurent Michel, Jacky Aboissière, Hakim Abdulhamid, Centre National de la Recherche Scientifique - CNRS (FRANCE), Ecole nationale supérieure des Mines d'Albi-Carmaux - IMT Mines Albi (FRANCE), Institut National des Sciences Appliquées de Toulouse - INSA (FRANCE), Institut Supérieur de l'Aéronautique et de l'Espace - ISAE-SUPAERO (FRANCE), Sogeti (FRANCE), Université Toulouse III - Paul Sabatier - UT3 (FRANCE), Institut Clément Ader (ICA), Institut Supérieur de l'Aéronautique et de l'Espace (ISAE-SUPAERO)-Institut National des Sciences Appliquées - Toulouse (INSA Toulouse), Institut National des Sciences Appliquées (INSA)-Université de Toulouse (UT)-Institut National des Sciences Appliquées (INSA)-Université de Toulouse (UT)-Université Toulouse III - Paul Sabatier (UT3), Université de Toulouse (UT)-Centre National de la Recherche Scientifique (CNRS)-IMT École nationale supérieure des Mines d'Albi-Carmaux (IMT Mines Albi), Institut Mines-Télécom [Paris] (IMT)-Institut Mines-Télécom [Paris] (IMT), Institut National des Sciences Appliquées - Toulouse (INSA Toulouse), Institut National des Sciences Appliquées (INSA)-Institut National des Sciences Appliquées (INSA)-Centre National de la Recherche Scientifique (CNRS)-Université Toulouse III - Paul Sabatier (UT3), Université Fédérale Toulouse Midi-Pyrénées-Université Fédérale Toulouse Midi-Pyrénées-IMT École nationale supérieure des Mines d'Albi-Carmaux (IMT Mines Albi), and Institut Mines-Télécom [Paris] (IMT)-Institut Mines-Télécom [Paris] (IMT)-Institut Supérieur de l'Aéronautique et de l'Espace (ISAE-SUPAERO)

Subjects
Ply drop-off, Materials science, Matériaux, Composite number, Damage tolerance, Failure mechanism, Composite, 02 engineering and technology, 010402 general chemistry, 01 natural sciences, [SPI.MAT]Engineering Sciences [physics]/Materials, Discontinuity (geotechnical engineering), Compression after impact, Composite material, Civil and Structural Engineering, business.industry, Structural engineering, 021001 nanoscience & nanotechnology, 0104 chemical sciences, Compressive load, Residual strength, Impact, Ceramics and Composites, Point location, 0210 nano-technology, business, Neutral axis
Abstract

International audience; This paper presents an experimental study of CAI (compression after impact) of tapered composite laminate. Two types of layup with thickness changing from 4 mm to 6 mm are considered. A new CAI testing rig, suitable for the specimens and a brief description of impact damage are presented first. Then, the behavior of impacted specimens under compressive loading is discussed along with the effects of ply drop-off parameters (taper angle, ply drop-off disposition and configuration) and impact point location on the failure mechanism. Finally, the residual strength in CAI of tapered laminates is compared with equivalent flat laminates. The results show that compressive behavior of the specimens is mostly governed by a coupling between compression and bending, generated by the discontinuity of the neutral axis in the tapered region. Despite this difference of behavior with flat laminates, the presence of ply drop-off has little effect on the residual strength in CAI.

Published
2016
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6. Experimental analysis of CFRP laminates subjected to compression after edge impact

Author

Christophe Bouvet, Benjamin Ostré, Clément Minot, Jacky Aboissière, Institut Clément Ader (ICA), Institut Supérieur de l'Aéronautique et de l'Espace (ISAE-SUPAERO)-Institut National des Sciences Appliquées - Toulouse (INSA Toulouse), Institut National des Sciences Appliquées (INSA)-Université de Toulouse (UT)-Institut National des Sciences Appliquées (INSA)-Université de Toulouse (UT)-Université Toulouse III - Paul Sabatier (UT3), Université de Toulouse (UT)-Centre National de la Recherche Scientifique (CNRS)-IMT École nationale supérieure des Mines d'Albi-Carmaux (IMT Mines Albi), Institut Mines-Télécom [Paris] (IMT)-Institut Mines-Télécom [Paris] (IMT), Sogeti (FRANCE), Centre National de la Recherche Scientifique - CNRS (FRANCE), Ecole nationale supérieure des Mines d'Albi-Carmaux - IMT Mines Albi (FRANCE), Institut National des Sciences Appliquées de Toulouse - INSA (FRANCE), Institut Supérieur de l'Aéronautique et de l'Espace - ISAE-SUPAERO (FRANCE), Université Toulouse III - Paul Sabatier - UT3 (FRANCE), Département de Mécanique des Structures et Matériaux - DMSM (Toulouse, France), Institut National des Sciences Appliquées - Toulouse (INSA Toulouse), Institut National des Sciences Appliquées (INSA)-Institut National des Sciences Appliquées (INSA)-Centre National de la Recherche Scientifique (CNRS)-Université Toulouse III - Paul Sabatier (UT3), Université Fédérale Toulouse Midi-Pyrénées-Université Fédérale Toulouse Midi-Pyrénées-IMT École nationale supérieure des Mines d'Albi-Carmaux (IMT Mines Albi), and Institut Mines-Télécom [Paris] (IMT)-Institut Mines-Télécom [Paris] (IMT)-Institut Supérieur de l'Aéronautique et de l'Espace (ISAE-SUPAERO)

Subjects
Materials science, business.industry, Matériaux, Damage tolerance, 02 engineering and technology, Structural engineering, Fibre-reinforced plastic, Edge (geometry), 021001 nanoscience & nanotechnology, Residual, Compression (physics), Residual strength, Stress (mechanics), 020303 mechanical engineering & transports, Compressive strength, Edge impact, 0203 mechanical engineering, [SPI.MECA.MEMA]Engineering Sciences [physics]/Mechanics [physics.med-ph]/Mechanics of materials [physics.class-ph], Ceramics and Composites, Compression after impact, Composite material, 0210 nano-technology, business, Civil and Structural Engineering
Abstract

International audience; Composite structures are particularly vulnerable to impact which lowers drastically theirs residual strength. In particular, the edge impact on composite stiffener is known as a critical factor on the loss of residual compression strength. At the same time, manufacturing of stiffened panels and achievement of experimental tests, of edge impact and compression after edge impact (CAEI) with stiffened panel, are particularly complex and costly. Then an experimental test set up has been designed to easily study the edge impact and the CAEI without complex specimen. It avoids the complex manufacturing of stiffener panels and avoids the use of high capacity machine. The mean goal is to define a new design method to improve the edge impact damage tolerance.Then experimental analysis of CAEI has been carried out on carbon fibre reinforced plastic (CFRP) laminates. This paper presents these results in order to determine the residual properties of the structure and to elaborate the failure scenario. It seems that a propagation of a compressive fibre failure plays a major role in the mechanisms that drives the laminate residual strength after edge impact. The good agreement of an open hole model with point stress approach seems to confirm the major role of the compressive fibre failure in the final failure.

Published
2016
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7. Edge impact modeling on stiffened composite structures

Author

Clément Minot, Jacky Aboissière, Christophe Bouvet, Benjamin Ostré, Institut Clément Ader (ICA), Institut National des Sciences Appliquées - Toulouse (INSA Toulouse), Institut National des Sciences Appliquées (INSA)-Institut National des Sciences Appliquées (INSA)-Centre National de la Recherche Scientifique (CNRS)-Université Toulouse III - Paul Sabatier (UT3), Université Fédérale Toulouse Midi-Pyrénées-Université Fédérale Toulouse Midi-Pyrénées-IMT École nationale supérieure des Mines d'Albi-Carmaux (IMT Mines Albi), Institut Mines-Télécom [Paris] (IMT)-Institut Mines-Télécom [Paris] (IMT)-Institut Supérieur de l'Aéronautique et de l'Espace (ISAE-SUPAERO), Sogeti (FRANCE), Ecole nationale supérieure des Mines d'Albi-Carmaux - IMT Mines Albi (FRANCE), Institut National des Sciences Appliquées de Toulouse - INSA (FRANCE), Institut Supérieur de l'Aéronautique et de l'Espace - ISAE-SUPAERO (FRANCE), Université Toulouse III - Paul Sabatier - UT3 (FRANCE), Département de Mécanique des Structures et Matériaux - DMSM (Toulouse, France), Institut Supérieur de l'Aéronautique et de l'Espace (ISAE-SUPAERO)-Institut National des Sciences Appliquées - Toulouse (INSA Toulouse), Institut National des Sciences Appliquées (INSA)-Université de Toulouse (UT)-Institut National des Sciences Appliquées (INSA)-Université de Toulouse (UT)-Université Toulouse III - Paul Sabatier (UT3), Université de Toulouse (UT)-Centre National de la Recherche Scientifique (CNRS)-IMT École nationale supérieure des Mines d'Albi-Carmaux (IMT Mines Albi), and Institut Mines-Télécom [Paris] (IMT)-Institut Mines-Télécom [Paris] (IMT)

Subjects
Materials science, Impact behavior, 02 engineering and technology, Edge (geometry), 0203 mechanical engineering, Damage mechanics, Indentation, Point (geometry), Finite element modeling, Civil and Structural Engineering, business.industry, Structural engineering, Strain rate, Fibre-reinforced plastic, 021001 nanoscience & nanotechnology, Compression (physics), Discrete Ply Model, Finite element method, Mécanique des structures, 020303 mechanical engineering & transports, [SPI.MECA.STRU]Engineering Sciences [physics]/Mechanics [physics.med-ph]/Structural mechanics [physics.class-ph], Ceramics and Composites, Carbon fiber, 0210 nano-technology, business
Abstract

International audience; Finite Element Analysis of low velocity/low energy edge impact has been carried out on carbon fiber reinforced plastic structure. Edge impact experimental results were then compared to the numerical ‘‘Discrete Ply Model’’ in order to simulate the edge impact damage. This edge impact model is inspired to out-of-plan impact model on a laminate plate with addition of new friction and crushing behaviors.From a qualitative and quantitative point of view, this edge impact model reveals a relatively good experiment/model agreement concerning force–time and force–displacement curves, damage morphology or permanent indentation after impact. In particular the correlation is faithful concerning the results of the parameters retained by industry; the maximum crack length on the edge and the permanent indentation.Finally, it can be noticed that the model quickly answers in crushing mode and goes in an inadequate way from the dynamic behavior to the quasi-static behavior. In order to correct this problem it seems necessary to implement a strain rate effect in the behavior law on the fiber failure in compression. The next step is to apply this model to the compression after impact.

Published
2015
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