Author: "Christophe Bouvet" - Searchworks@Jio Institute Digital Library Search Results

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1. Multiaxial loading of aeronautic composite structures at intermediate scale: A review of VERTEX developments

Author: Bruno Castanié, Jean-Charles Passieux, Jean-Noel Périé, Christophe Bouvet, John-Eric Dufour, and Joël Serra
Subjects: Testing, Multiaxial loading, Digital image correlation, Composite Structures, Materials of engineering and construction. Mechanics of materials, TA401-492
Abstract: The certification of aeronautical composite structures is based on a pragmatic approach, which is intended to be safe and essentially experimental but with a strong test/calculation dialogue called the “Test Pyramid”. However, this has proved to be extremely expensive and it appears necessary to reduce its cost either by developing Virtual testing, or by developing richer tests on an intermediate scale between coupon specimens and structural parts. It was in the aim of meeting this objective that the VERTEX program (French acronym for “Experimental modeling and Validation of compositE strucTures under complEX loading”) was launched in 2012. After positioning the VERTEX program in relation to the literature, this review will explain the methodology and present the measurement methods specifically developed for this scale. Then, three scientific themes that have been studied will be detailed (large notches, impact and wrinkling case studies). Finally, a proposal for validating the structures using envelope curves will be put forward, an assessment made, and perspectives presented.
Published: 2024
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2. Testing Structural Elements under Multiaxial Loading: A Numerical Model of the Bench to Understand and Predict Complex Boundary Conditions

Author: Florent Grotto, Oscar Peta, Christophe Bouvet, Bruno Castanié, and Joël Serra
Subjects: composite structure, airworthiness certification, pyramid of tests, intermediate scale experiment, multiaxial loading, Motor vehicles. Aeronautics. Astronautics, TL1-4050
Abstract: Airworthiness certification requires proof of structure strength, which is performed generally through a building block approach. To achieve this, representative intermediate-scale experiments generated by test benches are, in general, needed, in addition to material characterization on a coupons scale and structure testing on a large scale. The VERTEX test bench can generate the combined loading of tension/compression-shear-pressure on structural elements and was modelled with Finite Elements to perform virtual testing, representative of its intermediate-scale specificity. The numerous bolted joints of the bench were modelled and their behavior was identified in previous tests, so the model could quantitatively estimate the transfer function of the bench, which is the relationship between the displacements imposed by the jacks and the resulting loads on a given sample. The VERTEX model was identified to represent load shapes and amplitudes based on a training set and was later confronted by a validation set of tests of tension and shear. A model with ideal boundary conditions was also developed for a comparison, but it failed to predict some load shape specificities and did not give any indication of the loading amplitude. Application cases of the developed model are shown to assess a range of virtual testing possibilities.
Published: 2024
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3. Design and Testing of Impacted Stiffened CFRP Panels under Compression with the VERTEX Test Rig

Author: Florent Grotto, Christophe Bouvet, Bruno Castanié, and Joël Serra
Subjects: stiffened panel, compression after impact, stiffener debonding, post-buckling, experiments, numerical simulations, Motor vehicles. Aeronautics. Astronautics, TL1-4050
Abstract: Aeronautical composite primary structures must evidence sufficient residual strength in the presence of damage for compliance with damage tolerance requirements. The study of stiffener debonding on panels subjected to compression after impact is performed in that scope. Compression leads to the buckling of the skin between the stiffeners, and thus a complex loading of the bonding between the skin and the stiffener. This paper describes the development of a stiffened specimen for the VERTEX multiaxial test rig as a first step towards the study of the damage tolerance evaluation of stiffened structures, under combined loadings and at the intermediate scale of the test pyramid. By using virtual testing, the specimen was designed to produce the phenomenology of interest as the first damage, i.e., the debonding of the stiffener from the centre. Three samples were manufactured and subjected to low velocity impacts at various locations and energies. Then the three samples were subjected to compression after impact, up to the stiffener debonding, under a post-buckling regime of the skin. Test loading evolution is described with force fluxes and global strains, obtained from in situ stereo-correlation. The different impacts were found to give different types of damage but similar residual strength to compression after impact.
Published: 2023
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4. Review of composite sandwich structure in aeronautic applications

Author: Bruno CASTANIE, Christophe BOUVET, and Malo Ginot
Subjects: Composite, Sandwich structures, Aeronautic, Materials of engineering and construction. Mechanics of materials, TA401-492
Abstract: This paper presents a review of the issues concerning sandwich structures for aeronautical applications. The main questions raised by designers are first recalled and the complexity of sandwich structure design for aeronautics is highlighted. Then a review of applications is presented, starting with early examples from the 1930s and the Second World War. The growth in the use of sandwich materials in civil and military applications is then developed. Recent research and innovations conclude the paper.
Published: 2020
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5. Study of translaminar fracture toughness of unidirectional flax/epoxy composite

Author: Yousef Saadati, Gilbert Lebrun, Christophe Bouvet, Jean-François Chatelain, and Yves Beauchamp
Subjects: Flax fiber, Translaminar fracture energy, Fracture toughness, Flax-epoxy composites, Tensile and compressive translaminar fracture, Infrared thermography, Materials of engineering and construction. Mechanics of materials, TA401-492
Abstract: Ever growing applications of flax fiber-reinforced composites (FFRCs) and their suitability for structural uses involve implementing the design and failure criteria for these composites. Translaminar fracture is one of the primary failure modes of unidirectional (UD) fiber-reinforced composites, and measuring it is essential for design purposes and in many material failure studies. However, the translaminar fracture parameters have not been evaluated for UD-FFRCs; thus, there is no data available in the literature. Moreover, conventional test methods for this failure mode are complex, and there is no standard method for measuring this value in compression. In this study, the translaminar fracture behavior of a UD flax/epoxy composite has been examined, and its fracture toughness in tension and compression in the fiber direction are determined following existing standard methods as well as using a methodology developed using infrared thermography. Compact tension specimens were adapted and used for this purpose. A fractographic study is conducted to examine the fracture surfaces and better understand the failure mechanisms. For tensile tests, the results of infrared thermography are in good agreement with those of ASTM E1922 and lie in the range of values obtained for similar composites in the literature.
Published: 2020
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6. Evaluation of the Impact Resistance of Various Composite Sandwich Beams by Vibration Tests

Author: Amir Shahdin, Joseph Morlier, Laurent Mezeix, Christophe Bouvet, and Yves Gourinat
Subjects: Physics, QC1-999
Abstract: Impact resistance of different types of composite sandwich beams is evaluated by studying vibration response changes (natural frequency and damping ratio). This experimental works will help aerospace structural engineer in assess structural integrity using classification of impact resistance of various composite sandwich beams (entangled carbon and glass fibers, honeycomb and foam cores). Low velocity impacts are done below the barely visible impact damage (BVID) limit in order to detect damage by vibration testing that is hardly visible on the surface. Experimental tests are done using both burst random and sine dwell testing in order to have a better confidence level on the extracted modal parameters. Results show that the entangled sandwich beams have a better resistance against impact as compared to classical core materials.
Published: 2011
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7. Translaminar Cracking Modeling in Woven-ply Thermoplastic Laminates in Tension and in Compression

Author: Juan Daniel Pujols Gonzalez, Christophe Bouvet, Benoit Vieille, Groupe de physique des matériaux (GPM), Université de Rouen Normandie (UNIROUEN), Normandie Université (NU)-Normandie Université (NU)-Institut national des sciences appliquées Rouen Normandie (INSA Rouen Normandie), Institut National des Sciences Appliquées (INSA)-Normandie Université (NU)-Institut National des Sciences Appliquées (INSA)-Centre National de la Recherche Scientifique (CNRS)-Institut de Recherche sur les Matériaux Avancés (IRMA), Université de Caen Normandie (UNICAEN), Normandie Université (NU)-Normandie Université (NU)-École Nationale Supérieure d'Ingénieurs de Caen (ENSICAEN), Normandie Université (NU)-Commissariat à l'énergie atomique et aux énergies alternatives (CEA)-Université de Rouen Normandie (UNIROUEN), Normandie Université (NU)-Institut national des sciences appliquées Rouen Normandie (INSA Rouen Normandie), Institut National des Sciences Appliquées (INSA)-Normandie Université (NU)-Institut National des Sciences Appliquées (INSA)-Centre National de la Recherche Scientifique (CNRS)-Université de Caen Normandie (UNICAEN), Normandie Université (NU)-École Nationale Supérieure d'Ingénieurs de Caen (ENSICAEN), Normandie Université (NU)-Commissariat à l'énergie atomique et aux énergies alternatives (CEA)-Centre National de la Recherche Scientifique (CNRS), 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), and Institut Mines-Télécom [Paris] (IMT)-Institut Mines-Télécom [Paris] (IMT)
Subjects: Ceramics and Composites, [SPI.MAT]Engineering Sciences [physics]/Materials
Abstract: International audience
Published: 2023
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8. Experimental behaviour of aeronautical notched carbon fibre reinforced thermoplastic panels under combined tension-shear-pressure loadings

Author: Florent Grotto, Christophe Bouvet, Bruno Castanié, Joël Serra, 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), and Institut Mines-Télécom [Paris] (IMT)-Institut Mines-Télécom [Paris] (IMT)
Subjects: [SPI]Engineering Sciences [physics], Engineering Failure Analysis, General Engineering, General Materials Science
Abstract: International audience; This is a PDF file of an article that has undergone enhancements after acceptance, such as the addition of a cover page and metadata, and formatting for readability, but it is not yet the definitive version of record. This version will undergo additional copyediting, typesetting and review before it is published in its final form, but we are providing this version to give early visibility of the article. Please note that, during the production process, errors may be discovered which could affect the content, and all legal disclaimers that apply to the journal pertain.
Published: 2023
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9. Contributors

Author: M. Ahmadi, Yehia Bahei-El-Din, A. Banerjee, Konstantinos P. Baxevanakis, Christophe Bouvet, J. Brechou, Juan Camilo Calle, A. Chanda, Tianyu Chen, Zhong Chen, J.D. Coe, Laurence A. Coles, R. Das, D.M. Dattelbaum, M. Fotouhi, Christopher M. Harvey, Paul J. Hazell, Md Niamul Islam, Young W. Kwon, Genevieve S. Langdon, Alejandro Maranon, G. Minak, N.K. Naik, Keiji Ogi, Juan Pablo Casas-Rodriguez, R. Panciroli, Vaibhav A. Phadnis, Christophe Pinna, Samuel Rivallant, Vicent Robinson, Anish Roy, Serag Salem, Andreas Schiffer, Mostafa Shazly, Yu Shi, Vadim V. Silberschmidt, Gregory M. Sinclair, Constantinos Soutis, Vito L. Tagarielli, Himayat Ullah, Chris J. von Klemperer, Chen Wang, Hongxu Wang, Simon Wang, and Shigeki Yashiro
Published: 2023
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10. High-speed infrared thermography for in-situ damage monitoring during impact test

Author: Julien Berthe, Salim Chaibi, Gérald Portemont, Pascal Paulmier, Frédéric Laurin, Christophe Bouvet, DMAS, ONERA [Lille], ONERA, DMAS, ONERA, Université Paris Saclay [Châtillon], ONERA-Université Paris-Saclay, 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), and Institut Mines-Télécom [Paris] (IMT)-Institut Mines-Télécom [Paris] (IMT)
Subjects: [PHYS]Physics [physics], [SPI]Engineering Sciences [physics], Infrared thermography Impact tests Damage Composite materials, Ceramics and Composites, [CHIM]Chemical Sciences, Civil and Structural Engineering
Abstract: International audience; The impact damage tolerance remains for laminated composite materials one of the critical step in the design of aeronautical structures. Due to couplings between the different involved damage mechanisms (transverse cracks, delamination, fibre failure), the determination of the damage scenarios is still very challenging considering only post-mortem controls, such as C-Scan or more recently CT-Scan. Therefore, the present study is dedicated to the real time measurement of the evolution of different damage mechanisms during low velocity / low energy impact tests using high-speed infrared thermography. Impact tests at different energy levels were conducted on a T700GC/M21 quasi-isotropic laminate in order to demonstrate for different damage scenarios of increasing complexity the contribution of this measurement technique and to extract valuable information in order to validate simulation. Various post-mortem observation techniques (SEM, C-scan and X-ray tomography) are used in this study to validate and/or determine the chronology of the various damage events identified with infrared thermography measurements. Finally the projected damaged areas have been estimated with IR-thermography at the end of impact tests, based on methodologies available in the literature, and compared with other classical postmortem measurement methods. This comparison highlights that the assessment of the extent of damage by IR thermography tends to overestimate the extent of damage.
Published: 2023
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11. Prédictions numériques de la tolérance aux dommages d'impact d'une structure composite soumise à des chargements complexes

Author: Joel Serra, Antoine Trellu, christophe bouvet, Samuel Rivallant, Léon Ratsifandrihana, Bruno Castanie, 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), Segula Technologies [France], Institut Supérieur de l'Aéronautique et de l'Espace (ISAE-SUPAERO), and Université Polytechnique Hauts-de-France [UPHF]
Subjects: Dialogue essais, [SPI]Engineering Sciences [physics], Impact, [SPI.MECA.STRU]Engineering Sciences [physics]/Mechanics [physics.med-ph]/Structural mechanics [physics.class-ph], Essais structuraux, Endommagement, Composite, Multiaxial, calculs
Abstract: International audience; Des sollicitations multiaxiales sur structures stratifiées composites impactées sont réalisées à l'aide d'un banc d'essais développé à l'Institut Clément Ader (Toulouse). Une modélisation ElémentsFinis ,le « Discrete Ply Model », est utilisée pour simuler le comportement à rupture de ces plaques composites. Les calculs explicites prennent en compte à la fois la sollicitation d'impact et le chargement multiaxial post-impact. Un suivi par caméras optiques et infrarouge est mis en place afin de valider les simulations numériques.
Published: 2022

12. Development of a 3D finite element model at mesoscale for the crushing of unidirectional composites: Application to plates crushing

Author: Florent Grotto, Samuel Rivallant, Christophe Bouvet, 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), and Université Toulouse III - Paul Sabatier - UT3 (FRANCE)
Subjects: Mécanique des structures, Ceramics and Composites, Crashworthiness, Energy absorption, Finite element analysis, Carbon UD laminate, Civil and Structural Engineering
Abstract: This paper presents the development of a new 3D finite element model for the simulation of UD composites materials under crushing, at the mesoscale. It is based on the Discrete Ply Model (DPM), enhanced with a new damage law to represent compression at constant stress due to localised crushing and its propagation from one element to another. The model aims to take into account the various damage types involved in UD laminates during crushing and the associated absorbed energies: delamination, splitting, ply rupture in tension or bending, compression due to localised fragmentation and friction. The model is confronted with experimental results obtained on laminated plates crushing: not only global metrics (force, energy absorbed…) but especially key morphological aspects of the crushing front (delamination lengths, splaying, number of plies under localised crushing, debris wedge…) thanks to high speed camera pictures.
Published: 2022

13. Numerical analysis of the mechanical behaviour of an entangled cross-linked fibrous network

Author: Fadhel Chatti, Christophe Bouvet, Dominique Poquillon, 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), Centre interuniversitaire de recherche et d'ingenierie des matériaux (CIRIMAT), Université Toulouse III - Paul Sabatier (UT3), Université de Toulouse (UT)-Université de Toulouse (UT)-Institut de Chimie du CNRS (INC)-Centre National de la Recherche Scientifique (CNRS)-Institut National Polytechnique (Toulouse) (Toulouse INP), and Université de Toulouse (UT)
Subjects: Fibrous material, [SPI.MECA.STRU]Engineering Sciences [physics]/Mechanics [physics.med-ph]/Structural mechanics [physics.class-ph], [SPI.MECA.MEMA]Engineering Sciences [physics]/Mechanics [physics.med-ph]/Mechanics of materials [physics.class-ph], Mechanical behaviour, [SPI.MECA.MSMECA]Engineering Sciences [physics]/Mechanics [physics.med-ph]/Materials and structures in mechanics [physics.class-ph], [SPI.MECA.SOLID]Engineering Sciences [physics]/Mechanics [physics.med-ph]/Solid mechanics [physics.class-ph], Entangled cross-linked material, Numerical model
Abstract: International audience; A numerical model of the mechanical behaviour of a fibrous material made of carbon fibres cross-linked with a spray of epoxy resin has been developed. This model makes it possible to study the effect of some morphological or mechanical parameters. The size of the representative volume element (RVE) was evaluated for it to be representative of the used fibrous material. The model made it possible to study the effect of the fibre diameter and the Young’s modulus of the distance between junctions or of the volume fraction. The increasing of the compressive Young’s modulus is an important goal to use the proposed fibrous material as core material for a sandwich structure. The proposed model shows that an important gain is possible if the manufacturing process is better controlled, in particular if the fibre tows are better separated or if the fibre orientation is more isotropic.
Published: 2022
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14. Numerical simulations of combined size effects acting on an open-hole laminated composite plate under tension

Author: Joel Serra, Christophe Bouvet, Prajwal Karinja Haridas, Léon Ratsifandrihana, 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), and Segula Technologies [France]
Subjects: Finite Element Model, Mechanics of Materials, Mechanical Engineering, [SPI.MECA.MEMA]Engineering Sciences [physics]/Mechanics [physics.med-ph]/Mechanics of materials [physics.class-ph], Materials Chemistry, Ceramics and Composites, Discrete Ply Modeling, Size effect, Thickness effect, Open-hole tensile test, Blocked plies
Abstract: International audience; Numerical and experimental research programs have been carried out to investigate the effect of scaling on the tensile strength of notched composites. This paper presents a computational study of scaled open-hole tensile tests using the Discrete Ply Model (DPM) method. This finite element model is discrete, and only a small number of parameters are required from experimental characterization tests. Experimental and numerical strength values are compared here, and reveal that DPM simulations tend to slightly overestimate strength values, with an average discrepancy of 9.7%. However, DPM Results show that such modeling simulates both the reduction in strength when specimen size is increased for sublaminate level scaled specimens, where failure is fiber dominated, and the increase in strength when specimen size is increased for ply level scaled specimens, where failure is delamination dominated. In all cases, increasing the total thickness of the specimen leads to a decrease in strength and this effect is dominant over the effect of increasing hole diameter. As well as the variation in strength, three distinct failure mechanisms are observed: fiber failure with extensive matrix damage (pull-out failure), fiber failure with little or no matrix damage (brittle failure) and delamination failure. Comparisons with experiments demonstrate that tensile strengths, damage propagation scenarios and failure patterns are predicted with acceptable accuracy.
Published: 2022
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15. Contributors

Author: Mir Karim Razavi Aghjeh, Kamel Berkache, Emanuela Bosco, Christophe Bouvet, Fadhel Chatti, Vincenzo Cucumazzo, Nik Dave, Jean-Francois Ganghoffer, Marc G.D. Geers, Carlos González, Alp Karakoç, Artem Kulachenko, Javier Llorca, Horacio Lopez-Menendez, Yanhui Ma, Rami Mansour, Francisca Martínez-Hergueta, Ron H.J. Peerlings, Dominique Poquillon, Amit Rawal, Mir Jalil Razavi, Hilal Reda, Alvaro Ridruejo, Noud P.T. Schoenmakers, Vadim V. Silberschmidt, Emrah Sozumert, Tetsu Uesaka, and Hanxing Zhu
Published: 2022
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16. Combined loadings after medium velocity impact on large CFRP laminated plates: Discrete ply model simulations

Author: L. Ratsifandrihana, Antoine Trellu, Joël Serra, Bruno Castanié, Christophe Bouvet, Samuel Rivallant, 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), Segula Technologies (FRANCE), Département de Mécanique des Structures et Matériaux - DMSM (Toulouse, 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), and Segula Technologies [France]
Subjects: Combined loading, Work (thermodynamics), Structural testing, Materials science, Composite structures, business.industry, Mechanical Engineering, Composite number, Test rig, Structural engineering, Impact test, Medium velocity impact, [SPI]Engineering Sciences [physics], Mécanique des structures, Mechanics of Materials, Numerical modeling, TA401-492, Ceramics and Composites, Virtual test, Boundary value problem, business, Materials of engineering and construction. Mechanics of materials
Abstract: International audience; To decrease development costs of aeronautical composite structures, industrials and academic researchers are turning to “virtual testing” methods. To help achieve this objective, a new methodology has been developed at the Institut Clément Ader. It is based on a complex loading test rig for technological specimens (more representative than the usual level of coupons) and the Discrete Ply Model (DPM), a model allowing the main damage occurring in composite structures to be simulated. This research focuses on the combined loading of CFRP plates after impact. In a previous work, plates were experimentally impacted and loaded after the impact in the VERTEX test rig and a methodology to transfer boundary conditions to the numerical model was validated using a simple model without damage. In the work presented here, the DPM was used to simulate both the impact and the complex loading after impact tests. Numerical results and experimental results showed satisfactory correlation. The research undertaken demonstrates that the impact damage has very little influence when the tests are performed at larger scales than coupons. It is therefore paramount to use a pyramidal approach to design and test composite structures, in order to avoid oversizing.
Published: 2021
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17. Benchmark of wrinkling formulae and methods for pre-sizing of aircraft lightweight sandwich structures

Author: Michele D'Ottavio, Olivier Polit, Bruno Castanié, Christophe Bouvet, M. Ginot, Elixir Aircraft, Laboratoire Energétique Mécanique Electromagnétisme (LEME), Université Paris Nanterre (UPN), 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), Elixir Aircraft (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), Institut Mines-Télécom [Paris] (IMT)-Institut Mines-Télécom [Paris] (IMT)-Institut Supérieur de l'Aéronautique et de l'Espace (ISAE-SUPAERO), 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), Université Paris Ouest Nanterre La Défense (FRANCE), Institut National des Sciences Appliquées (INSA)-Université Fédérale Toulouse Midi-Pyrénées-Institut National des Sciences Appliquées (INSA)-Université Fédérale Toulouse Midi-Pyrénées-Université Toulouse III - Paul Sabatier (UT3), and Université Fédérale Toulouse Midi-Pyrénées-Centre National de la Recherche Scientifique (CNRS)-IMT École nationale supérieure des Mines d'Albi-Carmaux (IMT Mines Albi)
Subjects: Computer science, 02 engineering and technology, [SPI.MECA.MSMECA]Engineering Sciences [physics]/Mechanics [physics.med-ph]/Materials and structures in mechanics [physics.class-ph], Benchmark, Composite beams, Stress (mechanics), 0203 mechanical engineering, Simple (abstract algebra), Sandwich structures, ComputingMilieux_MISCELLANEOUS, Light aviation, Civil and Structural Engineering, business.industry, Structural engineering, 021001 nanoscience & nanotechnology, Wrinkling, Sizing, Finite element method, Compressive load, Mécanique des structures, 020303 mechanical engineering & transports, Buckling, Ceramics and Composites, Benchmark (computing), 0210 nano-technology, business
Abstract: Sandwich structures are widely used in many industrial applications and especially in light aviation. The local buckling phenomenon named “wrinkling” is one of the primary causes of compressive failure of such structures. Its calculation is a difficult practical problem since this phenomenon cannot be captured by the GFEM (Global Finite Element Model) classically used for aircraft structure sizing. Therefore, pre-sizing involves the use of a wrinkling model, which can be found in the literature. In practice, such models are used with high safety factors by the industry. This paper proposes an evaluation of analytical wrinkling formulas in an industrial setting. Realistic applications involve a framework (3D stress state, orthotropy, skin asymmetry) far from the assumptions on which most of the analytical formulations are based. The case study is a sandwich composite beam subjected to uni-axial compressive load. Limitations and assumptions of the analytical wrinkling models studied are quantified and a discussion on the relevance of using simple formulas for the design of sandwich structured composites is developed.
Published: 2021
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18. Failure simulation of four point bending CFRP laminate specimen including wrinkles

Author: Bruno Castanié, Pierre Journoud, christophe bouvet, Léon Ratsifandrihana, 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), Segula Technologies, 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.MECA.MSMECA]Engineering Sciences [physics]/Mechanics [physics.med-ph]/Materials and structures in mechanics [physics.class-ph]
Abstract: International audience; The influence of manufacturing defects in laminated composites is an major field of research according to their detrimental effects on the residual strength of the structure [1]. Among the different types of defects, wrinkling and waviness are perhaps one of the most common and detrimental, especially under compression. Here the term “waviness” is used to describe in-plane misalignment of fibers and the term “wrinkling” refers to out-of-plane misalignment of fibers. In the literature, wrinkling in a planar part is massively studied [2-3] but to our knowledge, less interest was paid to the influence of wrinkling present in the radius of a curved part. In this paper, a numerical study the influence of wrinkles contained in the radius of L-shape specimen tested under four-point bending tests is done. The used model called ‘Discrete Ply Model’ (DPM) and developed at Institut Clement Ader [4–6] a decade ago [4–6], which has already demonstrated its capability to give a good agreement between experimental results and simulation of four points bending tests without wrinkles [7]. Several specimens with different severities of wrinkling were manufactured. Concave moulds were used with two strategies of stacking. The first one consists classically to lay in the concave mould the different plies to obtain the stacking desired without defect. The second method permits to introduce wrinkling of plies and consists in realizing the staking on a table and afterwards introducing the package in the mould. Depending on the number of plies previously stacked on the table, the wrinkles observed are more or less significant. By combining these two methods, the intensity of wrinkling created can be adjusted and regulated. This strategy produced good results when the number of plies initially stacked on a flat surface is low. When too much plies are used to insert wrinkling under the radius of curvature of the part, the defects created are too serious and many voids emerge caused by wrinkling of plies. Four points bending tests on the different specimens produced were carried out. Digital images correlation and infrared thermographic imaging were used simultaneously to follow the damage of specimens. This instrumentation has enabled to capture the scenario of failure of L-angle shapes with presence of wrinkling under the radius of curvature. Finally, the DPM was used to numerically simulate the tests previously mentioned taking into consideration the ply wrinkling experimentally observed. For that, a range of points corresponding to the interface of the different plies was measured and used to create a mesh, which perfectly corresponds to the specimen
Published: 2021

19. Structural testing of large notched composite specimens under combined shear and pressure

Author: Florent Grotto, Joel Serra, christophe bouvet, Bruno Castanié, 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), 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.MECA.MSMECA]Engineering Sciences [physics]/Mechanics [physics.med-ph]/Materials and structures in mechanics [physics.class-ph]
Abstract: International audience; The VIRTUOSE project aims at reducing the number of experiments from the test pyramid that is necessary to certify aeronautical composite structures. Thanks to the VERTEX test rig [1, 2], a combined loading of tension/compression-shear-pressure can be applied on large specimens (400*400mm2 area of interest). Around the world, only few test rigs allow testing of structural specimens under multiaxial loadings. At a component level, between the coupon level and the assembly level, representative loadings are enforced on a large notched specimen representative of a composite fuselage section. The specimens are manufactured with 13 plies of unidirectional carbon/epoxy prepreg. Three notched panels with various stacking sequences are submitted to shear until failure. Three matching specimens are tested under shear up to failure with an additional initial internal pressure. Based on previous studies [1-3], methods of measurement have been developed to characterize global strains and loads fluxes undergone by the structure. Digital image stereo-correlation on the upper skin of the specimen is used to get full displacements fields. Once the curvature has been computed, the laminate theory allows the assessment of the fields of membrane stresses, in-plane loads and moment fluxes. Fluxes characterization on the specimen ends is of the utmost importance for industrial partners because the load cases used to size such panels are based on maximal allowable fluxes. The influence of the additional internal pressure on the failure scenario of the three different stacking sequences has been thoroughly analysed. Infrared thermography helped to clarify the failure chronology
Published: 2021

20. On the efficiency of some analytic wrinkling models

Author: Bruno Castanié, Malo Ginot, christophe bouvet, 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), Elixir Aircraft, 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), and Elixir Aircraft (FRANCE)
Subjects: [SPI.MECA.MSMECA]Engineering Sciences [physics]/Mechanics [physics.med-ph]/Materials and structures in mechanics [physics.class-ph]
Abstract: International audience; The design of very lightweight aircraft sandwich structured composites requires a deep knowledge to tackle the failure modes. In this paper, we focus on the wrinkling which may be the primary cause of failure of such structures. Currently, lightweight sandwich structured composites are more and more used in the aeronautics industry and extend to primary structures such as control surfaces [1]. The engineer therefore needs an efficient and effective tool to prevent the occurrence of wrinkling. The ideal, from the engineer’s point of view, would be to define the local buckling phenomenon using an analytical formulation with as few parameters as possible. As a result, the formulation proposed by Hoff and Maunter in 1945 [2] for wrinkling in sandwich beams is still widely used today as it only depends on 3 parameters. However, modelling the complex behaviour of local buckling in a sandwich structure using a simple analytical formulation is not easy. Strong assumptions are required to linearize the system of equations and obtain a simple form expression. A telling example is the approach of Douville and Grognec [3]. The authors start from a complex 3D base and then linearize their system by reporting the problem in an isotropic 2D framework. It is understood that analytical modelling allows a simple and quick use, which ideal for the engineers. However, this comes at the price of important assumptions, sometimes far from reality. Here, a critical literature review of analytical wrinkling formulations is done (for example [2-5]), and the equations are compared first to 3D finite element models and then to a coupon’s tests campaign. About fifty sandwich coupons panels, with a design consistent with those used in lightweight aeronautics sandwich structured composites, were tested. The onset of wrinkling under compressive uniaxial loading, thanks to Digital Image Correlation (DIC) and high-speed camera were captured. Finally, the limitations and approximations of the models are identified and the relevance of simple wrinkling formulas for the design of sandwich structured composites (anisotropy, defects etc...) are discussed.
Published: 2021

21. High temperature translaminar fracture of woven-ply thermoplastic laminates in tension and in compression

Author: Juan Daniel Pujols Gonzalez, Christophe Bouvet, Benoit Vieille, Groupe de physique des matériaux (GPM), Université de Rouen Normandie (UNIROUEN), Normandie Université (NU)-Normandie Université (NU)-Institut national des sciences appliquées Rouen Normandie (INSA Rouen Normandie), Institut National des Sciences Appliquées (INSA)-Normandie Université (NU)-Institut National des Sciences Appliquées (INSA)-Centre National de la Recherche Scientifique (CNRS)-Institut de Recherche sur les Matériaux Avancés (IRMA), Université de Caen Normandie (UNICAEN), Normandie Université (NU)-Normandie Université (NU)-École Nationale Supérieure d'Ingénieurs de Caen (ENSICAEN), Normandie Université (NU)-Commissariat à l'énergie atomique et aux énergies alternatives (CEA)-Université de Rouen Normandie (UNIROUEN), Normandie Université (NU)-Institut national des sciences appliquées Rouen Normandie (INSA Rouen Normandie), Institut National des Sciences Appliquées (INSA)-Normandie Université (NU)-Institut National des Sciences Appliquées (INSA)-Centre National de la Recherche Scientifique (CNRS)-Université de Caen Normandie (UNICAEN), Normandie Université (NU)-École Nationale Supérieure d'Ingénieurs de Caen (ENSICAEN), Normandie Université (NU)-Commissariat à l'énergie atomique et aux énergies alternatives (CEA)-Centre National de la Recherche Scientifique (CNRS), 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), 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 National des Sciences Appliquées - INSA (FRANCE), Centre National de la Recherche Scientifique (CNRS)-Institut national des sciences appliquées Rouen Normandie (INSA Rouen Normandie), Institut National des Sciences Appliquées (INSA)-Normandie Université (NU)-Institut National des Sciences Appliquées (INSA)-Normandie Université (NU)-Université de Rouen Normandie (UNIROUEN), Normandie Université (NU), 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: Digital image correlation, Thermoplastic, Materials science, 0211 other engineering and technologies, 02 engineering and technology, Woven-ply laminate Thermoplastic, [SPI.MAT]Engineering Sciences [physics]/Materials, Fracture toughness, 0203 mechanical engineering, [SPI.MECA.MEMA]Engineering Sciences [physics]/Mechanics [physics.med-ph]/Mechanics of materials [physics.class-ph], General Materials Science, Composite material, Critical energy release rate, ComputingMilieux_MISCELLANEOUS, 021101 geological & geomatics engineering, chemistry.chemical_classification, Tension (physics), Mechanical Engineering, Fracture mechanics, Composite laminates, Compression (physics), High temperature, Mécanique des structures, 020303 mechanical engineering & transports, Translaminar fracture toughness, chemistry, Mechanics of Materials, [SPI.MECA.STRU]Engineering Sciences [physics]/Mechanics [physics.med-ph]/Structural mechanics [physics.class-ph], Fracture (geology)
Abstract: The translaminar fracture behavior of three composite laminates, based on thermoplastic matrix PEEK reinforced by a woven carbon fibers obtained by consolidation process, has been studied by means of Compact Tension (CT) and Compact Compression (CC) tests. An orthotropic laminate and two quasi-isotropic laminates, have been tested at room temperature (RT) and at 150 °C (i.e. for a temperature slightly higher than the glass transition temperature Tg), with the purpose of evaluation the influence of the stacking sequence and the temperature on the damage mechanisms. The CT type tests show that the temperature influence on the overall mechanical response remains low. In contrast, the CC type tests show a decrease in the mechanical resistance and an augmentation in the global ductile behavior. By means of the 2D Digital Image Correlation and the implementation of a algorithm based on the sigma indicator (confidence interval in the area of interest), the crack propagation was measured during loading, then the G-R curves have been obtained from the compliance method. In tension, there is an increase in the translaminar fracture toughness with the laminate thickness and a slight improvement in this one due to the influence of temperature. In compression, the temperature strongly decreases the translaminar fracture toughness.
Published: 2021
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22. Experimental and Finite Element Analysis of the Tensile Behavior of Architectured Cu-Al Composite Wires

Author: Alireza Dashti, Clément Keller, Benoit Vieille, Christophe Bouvet, Alain Guillet, Groupe de physique des matériaux (GPM), Université de Rouen Normandie (UNIROUEN), Normandie Université (NU)-Normandie Université (NU)-Institut national des sciences appliquées Rouen Normandie (INSA Rouen Normandie), Institut National des Sciences Appliquées (INSA)-Normandie Université (NU)-Institut National des Sciences Appliquées (INSA)-Centre National de la Recherche Scientifique (CNRS)-Institut de Recherche sur les Matériaux Avancés (IRMA), Université de Caen Normandie (UNICAEN), Normandie Université (NU)-Normandie Université (NU)-École Nationale Supérieure d'Ingénieurs de Caen (ENSICAEN), Normandie Université (NU)-Commissariat à l'énergie atomique et aux énergies alternatives (CEA)-Université de Rouen Normandie (UNIROUEN), Normandie Université (NU)-Institut national des sciences appliquées Rouen Normandie (INSA Rouen Normandie), Institut National des Sciences Appliquées (INSA)-Normandie Université (NU)-Institut National des Sciences Appliquées (INSA)-Centre National de la Recherche Scientifique (CNRS)-Université de Caen Normandie (UNICAEN), Normandie Université (NU)-École Nationale Supérieure d'Ingénieurs de Caen (ENSICAEN), Normandie Université (NU)-Commissariat à l'énergie atomique et aux énergies alternatives (CEA)-Centre National de la Recherche Scientifique (CNRS), 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), Centre National de la Recherche Scientifique - CNRS (FRANCE), Ecole nationale supérieure des Mines d'Albi-Carmaux - IMT Mines Albi (FRANCE), Institut National Polytechnique de Toulouse - Toulouse INP (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 National des Sciences Appliquées - INSA (FRANCE), Normandie Université (FRANCE), Centre National de la Recherche Scientifique (CNRS)-Institut national des sciences appliquées Rouen Normandie (INSA Rouen Normandie), Institut National des Sciences Appliquées (INSA)-Normandie Université (NU)-Institut National des Sciences Appliquées (INSA)-Normandie Université (NU)-Université de Rouen Normandie (UNIROUEN), Normandie Université (NU), 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: Technology, Materials science, Modulus, 02 engineering and technology, Flow stress, 01 natural sciences, Article, [SPI]Engineering Sciences [physics], Autre, Residual stress, 0103 physical sciences, Ultimate tensile strength, [SPI.MECA.MEMA]Engineering Sciences [physics]/Mechanics [physics.med-ph]/Mechanics of materials [physics.class-ph], General Materials Science, Composite material, Tensile testing, 010302 applied physics, Microscopy, QC120-168.85, Wire drawing, QH201-278.5, Finite element analysis, 021001 nanoscience & nanotechnology, Engineering (General). Civil engineering (General), Cu-Al composite wires, TK1-9971, Descriptive and experimental mechanics, Volume fraction, Electrical engineering. Electronics. Nuclear engineering, TA1-2040, 0210 nano-technology, Rule of mixtures
Abstract: International audience; The present study investigates, experimentally and numerically, the tensile behavior of copper-clad aluminum composite wires. Two fiber-matrix configurations, the conventional Al-core/Cu-case and a so-called architectured wire with a continuous copper network across the cross-section, were considered. Two different fiber arrangements with 61 or 22 aluminum fibers were employed for the architectured samples. Experimentally, tensile tests on the two types of composites show that the flow stress of architectured configurations is markedly higher than that of the linear rule of mixtures’ prediction. Transverse stress components and processing-induced residual stresses are then studied via numerical simulations to assess their potential effect on this enhanced strength. A set of elastic-domain and elastoplastic simulations were performed to account for the influence of Young’s modulus and volume fraction of each phase on the magnitude of transverse stresses and how theses stresses contribute to the axial stress-strain behavior. Besides, residual stress fields of different magnitude with literature-based distributions expected for cold-drawn wires were defined. The findings suggest that the improved yield strength of architectured Cu-Al wires cannot be attributed to the weak transverse stresses developed during tensile testing, while there are compelling implications regarding the strengthening effect originating from the residual stress profile. Finally, the results are discussed and concluded with a focus on the role of architecture and residual stresses.
Published: 2021
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23. A new interface element connecting 3D finite elements with non-coincident nodes to simulate delamination in composite laminates

Author: Antoine Trellu, Christophe Bouvet, Léon Ratsifandrihana, Samuel Rivallant, 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), Segula Technologies (FRANCE), Département de Mécanique des Structures et Matériaux - DMSM (Toulouse, 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), SEGULA Technologies [Trappes], Segula Technologies [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: business.industry, Computer science, Crack propagation, Delamination, Fracture mechanics, 02 engineering and technology, Structural engineering, Composite laminates, 021001 nanoscience & nanotechnology, Compression (physics), Sizing, Finite element method, 020303 mechanical engineering & transports, 0203 mechanical engineering, Coincident, [SPI.MECA.MEMA]Engineering Sciences [physics]/Mechanics [physics.med-ph]/Mechanics of materials [physics.class-ph], Numerical modeling, Ceramics and Composites, Mécanique des matériaux, 0210 nano-technology, business, Interface element, Civil and Structural Engineering, Volume (compression)
Abstract: International audience; Composite failure phenomena remain complex and lead to over-size structures in many industries, involving long and costly experimental campaigns. Numerical approaches are a good alternative to decrease sizing costs. The Discrete Ply Model developed in Institut Clément Ader over these last ten years shows good results in simulation of impact and compression after impact of composite laminates, ply drop-offs, open hole tensile tests… But the present approach leads to certain limitations for complex stacking sequences and induces unwanted characteristic lengths between consecutive plies. A user element for delamination calculation is developed that allows to define an interface corresponding to the overlapping zone between the two volume elements of upper and lower plies, whereas this overlapping zone is not directly defined by nodes of the mesh (volume elements have non-coincident nodes). The present paper details the new interface element implementation, its validation from DCB and ENF test simulations, and then its improvement is discussed.
Published: 2020
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24. Influence of impact velocity on impact behaviour of hybrid woven-fibers reinforced PEEK thermoplastic laminates

Author: Benoit Vieille, thomas Breteau, Christophe Bouvet, Juan-Daniel Pujols Gonzalez, Christophe Gautrelet, Groupe de physique des matériaux (GPM), Université de Rouen Normandie (UNIROUEN), Normandie Université (NU)-Normandie Université (NU)-Institut national des sciences appliquées Rouen Normandie (INSA Rouen Normandie), Institut National des Sciences Appliquées (INSA)-Normandie Université (NU)-Institut National des Sciences Appliquées (INSA)-Centre National de la Recherche Scientifique (CNRS)-Institut de Recherche sur les Matériaux Avancés (IRMA), Université de Caen Normandie (UNICAEN), Normandie Université (NU)-Normandie Université (NU)-École Nationale Supérieure d'Ingénieurs de Caen (ENSICAEN), Normandie Université (NU)-Commissariat à l'énergie atomique et aux énergies alternatives (CEA)-Université de Rouen Normandie (UNIROUEN), Normandie Université (NU)-Institut national des sciences appliquées Rouen Normandie (INSA Rouen Normandie), Institut National des Sciences Appliquées (INSA)-Normandie Université (NU)-Institut National des Sciences Appliquées (INSA)-Centre National de la Recherche Scientifique (CNRS)-Université de Caen Normandie (UNICAEN), Normandie Université (NU)-École Nationale Supérieure d'Ingénieurs de Caen (ENSICAEN), Normandie Université (NU)-Commissariat à l'énergie atomique et aux énergies alternatives (CEA)-Centre National de la Recherche Scientifique (CNRS), 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 Rouen Normandie (INSA Rouen Normandie), Institut National des Sciences Appliquées (INSA)-Normandie Université (NU), Laboratoire de Mécanique de Normandie (LMN), Institut National des Sciences Appliquées (INSA)-Normandie Université (NU)-Institut National des Sciences Appliquées (INSA)-Normandie Université (NU), 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 National des Sciences Appliquées - INSA (FRANCE), Normandie Université (FRANCE), Laboratoire de Mécanique de Normandie - LMN (St Etienne du Rouvray, France), Centre National de la Recherche Scientifique (CNRS)-Institut national des sciences appliquées Rouen Normandie (INSA Rouen Normandie), Institut National des Sciences Appliquées (INSA)-Normandie Université (NU)-Institut National des Sciences Appliquées (INSA)-Normandie Université (NU)-Université de Rouen Normandie (UNIROUEN), Normandie Université (NU), 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: Thermoplastic, Materials science, Drop tower, Glass fiber, Charpy impact test, 02 engineering and technology, Polyether ether ketone, chemistry.chemical_compound, Permanent indentation, Impact velocity, 0203 mechanical engineering, Indentation, [SPI.MECA.MEMA]Engineering Sciences [physics]/Mechanics [physics.med-ph]/Mechanics of materials [physics.class-ph], Peek, Thermoplastic composite, Composite material, Charpy, Materials of engineering and construction. Mechanics of materials, chemistry.chemical_classification, Mechanical Engineering, Dissipation, 021001 nanoscience & nanotechnology, 020303 mechanical engineering & transports, Quasi-static indentation, chemistry, Mechanics of Materials, Ceramics and Composites, TA401-492, Mécanique des matériaux, 0210 nano-technology
Abstract: International audience; This study aims at examining the impact behavior of hybrid carbon and glass fibers woven-ply reinforced PolyEther Ether Ketone (PEEK) thermoplastic quasi-isotropic laminates. An instrumented Charpy pendulum is specifically designed to estimate its capability to perform low velocity impact tests. Through the comparison of different impact methods (Quasi-static indentation tests, Charpy and drop tower impacts), the influence of impact velocity on the impact behavior of this hybrid composite material is investigated. From the obtained results, it appears that the macroscopic impact response is similar in terms of force-displacement response. Indeed, the im- pact velocity is significantly higher (2.5 times higher) with falling weight impact testing. In PEEK-based laminates whose mechanical behaviour is time-dependent, slow loading rates (e.g. Charpy impact testing) are instrumental in ruling the dissipated energy ( + 20% at 35 and 40J) as well as in increasing the permanent indentation (1.6 times higher) that is always higher than the Barely Visible Impact Damage.
Published: 2020
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25. Strain rate effect of mode II interlaminar fracture toughness on the impact response of a thermoplastic PEEK composite

Author: Christophe Bouvet, Pablo Garcia-Perez, Joël Serra, 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 de Mécanique et d'Ingénierie (I2M), Université de Bordeaux (UB)-Institut Polytechnique de Bordeaux-Centre National de la Recherche Scientifique (CNRS)-Institut National de Recherche pour l’Agriculture, l’Alimentation et l’Environnement (INRAE)-Arts et Métiers Sciences et Technologies, HESAM Université - Communauté d'universités et d'établissements Hautes écoles Sorbonne Arts et métiers université (HESAM)-HESAM Université - Communauté d'universités et d'établissements Hautes écoles Sorbonne Arts et métiers université (HESAM), 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), HESAM Université (HESAM)-HESAM Université (HESAM), Arts et Métiers ParisTech (FRANCE), Centre National de la Recherche Scientifique - CNRS (FRANCE), Ecole nationale supérieure des Mines d'Albi-Carmaux - IMT Mines Albi (FRANCE), Institut national de recherche pour l'agriculture, l'alimentation et l'environnement - INRAE (FRANCE), Institut National des Sciences Appliquées de Toulouse - INSA (FRANCE), Institut Supérieur de l'Aéronautique et de l'Espace - ISAE-SUPAERO (FRANCE), Institut Polytechnique de Bordeaux - IPB (FRANCE), Université Toulouse III - Paul Sabatier - UT3 (FRANCE), and Université de Bordeaux (FRANCE)
Subjects: Thermoplastic, Materials science, Impact Delamination, Composite number, Thermosetting polymer, 02 engineering and technology, Strain rate effect, Carbon/PEEK composite, Fracture toughness, 0203 mechanical engineering, [SPI.MECA.MEMA]Engineering Sciences [physics]/Mechanics [physics.med-ph]/Mechanics of materials [physics.class-ph], Peek, Composite material, Materials of engineering and construction. Mechanics of materials, chemistry.chemical_classification, Mechanical Engineering, Epoxy, Strain rate, 021001 nanoscience & nanotechnology, Impact, 020303 mechanical engineering & transports, chemistry, Mechanics of Materials, Delamination, visual_art, TA401-492, Ceramics and Composites, visual_art.visual_art_medium, Mécanique des matériaux, 0210 nano-technology, Damage tolerance
Abstract: International audience; Recent advancements in composite production and processing are making thermoplastics a viable option in a wider array of aerospace applications. In particular, Carbon Fibre Reinforced Plastics (CFRP) with thermoplastic resin are believed to have better damage tolerance properties than thermosets. However, few studies have been conducted regarding the numerical modelling of the behaviour of such materials submitted to low energy impacts. Here the Discrete Ply Model (DPM), that predicts the failure of laminated composites with the help of cohesive elements, is used to compare thermosetting and thermoplastics impact damage tolerances. The DPM is improved to take into account the strain rate effect of the fracture toughness (FT) in mode II of interlaminar interfaces. First, the End Notched Flexure (ENF) test that induces unstable crack growth is used both to experimentally measure the value of FT in mode II for high speed crack growth and to identify the strain rate effect used in the model. Second, the DPM is then used to simulate impact tests for various stacking sequences ([45 2 , − 45 2 , 0 2 , 90 2 ] 2S , [0 2 , 45 2 , 90 2 , − 45 2 ] 2S , [0 2 , 30 2 , 90 2 , − 30 2 ] 2S and [90 2 , − 45 2 , 0 2 , 45 2 ] 2S ) and impact energy levels (10, 20 and 30 J). Good correlations with experiment are observed in terms of force/displacement curves and delaminated areas. The numerical model correctly describes the asymmetry of the delaminated interfaces and the propagation of groups of interfaces located near the mid-thickness of the laminated plates. Finally, the damage associated with a 30 J impact is compared for the carbon/PEEK of this study and classical carbon/epoxy plates using numerical simulations (DPM). No significant difference has been found. The results corroborate those obtained in previous studies showing the relatively low value of FT in mode II, using an ENF test and infrared thermography (IRT). This article therefore questions the apparent superiority of carbon/PEEK laminated composites over carbon/epoxy laminated composites in terms of impact damage tolerance.
Published: 2020
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26. Experimental and Numerical Study of Damages Induced by Low-Velocity Impact on 4th Generation Composite Laminates

Author: Dominique Martini, Johann Rannou, Salim Chaibi, Christophe Bouvet, Frédéric Laurin, Julien Berthe, Fabrice Congourdeau, DMAS, ONERA, Université Paris Saclay [Châtillon], ONERA-Université Paris-Saclay, 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), DMAS, ONERA [Lille], ONERA, Dassault Aviation, 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: [PHYS]Physics [physics], [SPI]Engineering Sciences [physics], Materials science, Damages, [CHIM]Chemical Sciences, Composite material, Composite laminates
Abstract: International audience; The use of composite fiber reinforced polymer (CFRP) structures in the aircraft industry needs to demonstrate that they satisfy the same safety requirements as for metal structures. Among these requirements, impact damage tolerance is a major sizing criterion for those structures. Impact induce complex out-of-plane loadings that results on large damage extensions. Experimental campaigns are realized at the industrial level to design composite structures but, it induces long and costly development for innovative solutions. Finite Element Model (FEM) is a good tool for sizing efficiently composite components even those exposed to impact. Unfortunately, numerical models developed by academics are too complex to be used in the industry. Besides, due to the highly non-linear problem, explicit solvers are used to avoid convergence issues, which require an expertise in the results verification. In this way, we present a damage model developed at the ONERA [1,2] to predict the progressive rupture of last generation composite laminates subjected to low-velocity impact (LVI)/low-energy impact (LEI). This model has been developed with a fair level of complexity in order to be used in aeronautical industries. This material has thick resin layers at each interface between each plies, which increase the toughness of the laminate. In order to understand damage mechanisms of this specific material when subjected to LVI/LEI, an investigation of impact damages has been carried out in this study. Since LVI/LEI do not enter in the scope of fast transient dynamics, we use an implicit integration scheme and the first results using the damage model are compared with the experimental data given by experimental testing.
Published: 2020
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27. Dimensionnement des trous et des assemblages dans les structures composites

Author: Christophe Bouvet
Abstract: Quelques methodologies classiques de dimensionnement des trous et des assemblages dans les structures composites sont ici presentees. Le dimensionnement de ces singularites est fondamental et doit souvent etre la premiere zone a prendre en compte dans la conception des structures composites primaires, c’est-a-dire celles supportant les efforts principaux. Apres une rapide presentation des methodes de dimensionnement des stratifies composites en zone courante, le dimensionnement des trous est aborde avec la methode du « point stress ». Puis le calcul des assemblages, a l’aide de la methode du flux d’effort equivalent, est presente ainsi que les limites des approches utilisees.
Published: 2020
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28. Influence of machining damage generated during trimming of CFRP composite on the compressive strength

Author: N. Nguyen-Dinh, Redouane Zitoune, Christophe Bouvet, 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), 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 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: Surface analysis, Materials science, Mechanical Engineering, Composite number, Mechanical testing, 02 engineering and technology, Composite materials, 021001 nanoscience & nanotechnology, Machining, 020303 mechanical engineering & transports, Compressive strength, Machined surface, 0203 mechanical engineering, Mechanics of Materials, [SPI.MECA.MEMA]Engineering Sciences [physics]/Mechanics [physics.med-ph]/Mechanics of materials [physics.class-ph], Materials Chemistry, Ceramics and Composites, Trimming, Mécanique des matériaux, Composite material, 0210 nano-technology, Anisotropy
Abstract: International audience; Machining of composite materials is a challenging task due to the heterogeneity and anisotropy of composite structures. The induced defects reduce integrity of the machined surface as well as the loading capacity of the composite structure in service. Therefore, it is necessary to quantify the damage induced during trimming and correlate the quality of the machined surface to mechanical properties. The correlation of the surface roughness criteria, widely used in literature, to the mechanical behavior raise several contradictions. For this reason, new parameters for the characterization of themachined surface are proposed and correlated to the mechanical behavior under compressive loading. In this context, carbon fiber-reinforced plastic laminates are conventionally trimmed, and the machining damage is characterized using scanning electron microscope observations, X-ray tomography, and 3D optical topography. The results reveal that crater volume and maximum depth of damage quantify the machining damage more realistic compared to the classical surface roughness criteria.
Published: 2020
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29. New tool for reduction of harmful particulate dispersion and to improve machining quality when trimming carbon/epoxy composites

Author: Mehdi Salem, N. Nguyen-Dinh, Akshay Hejjaji, Christophe Bouvet, Redouane Zitoune, 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), Thai Nguyen University of Technology (VIETNAM), Département de Mécanique des Structures et Matériaux - DMSM (Toulouse, France), 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), 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: Polymer-matrix composites (PMCs), Materials science, 02 engineering and technology, 010402 general chemistry, 01 natural sciences, Machining, Dust dispersion, Electron microscopy, Composite material, Tool wear, Respiratory hazard, Air contamination, Epoxy, Fibre-reinforced plastic, Particulates, 021001 nanoscience & nanotechnology, 0104 chemical sciences, [SPI.MECA.GEME]Engineering Sciences [physics]/Mechanics [physics.med-ph]/Mechanical engineering [physics.class-ph], Mechanics of Materials, visual_art, Ceramics and Composites, visual_art.visual_art_medium, Trimming, Defects, Mécanique des matériaux, 0210 nano-technology, Reduction (mathematics), Dispersion (chemistry)
Abstract: International audience; Conventional machining of carbon fiber reinforced plastic composites (CFRPs) generates minute chips that get suspended in air causing a hazard compromising operator safety. This study investigates the influence of cutting parameters (feed speed, cutting speed, radial depth of cut, tool geometry and tool wear) during trimming of CFRP on the form and quantity of harmful particles dispersed. Also, performance of two classical PCD tool geometries (two straight flutes, two helix flutes) have been compared with newly designed (in collaboration with ASAHI Company) four serrated straight flutes for the purpose of dust emission reduction. The quantification of the number of harmful particles was estimated using laser spectroscopic dust monitor. The results reveal that, trimming with a combination of higher feed speed and lower cutting speed can reduce the dispersion of harmful particles. Further, the four serrated straight flutes recorded the least number of harmful particles compared to the conventional tools.
Published: 2020
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30. Mécanique de la rupture de fibres dans les composites stratifiés

Author: Christophe Bouvet and Benoit Vieille
Abstract: Cet article propose une presentation de la mecanique de la rupture appliquee a la rupture translaminaire des composites stratifies. Ce phenomene est particulierement important dans le cadre de la certification des structures composites a la tolerance aux dommages. Apres un bref rappel des concepts de la mecanique de la rupture, les differents essais experimentaux caracterisant ces grandeurs seront presentes et commentes. Une revue detaillee des differents endommagements translaminaires sera ensuite effectuee puis quelques valeurs caracteristiques de tenacite a rupture de fibres seront discutees. Enfin la dissipation d’energie lors du crash, l’energie specifique absorbee (SEA), sera abordee.
Published: 2020
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31. Insert of sandwich panels sizing through a failure mode map

Author: Bruno Castanié, Juan de Dios Rodriguez-Ramirez, Christophe Bouvet, 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 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), 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: Insert (composites), Inserts, Computer science, business.industry, 02 engineering and technology, Sandwich panel, Structural engineering, 021001 nanoscience & nanotechnology, Sizing, Term (time), Nonlinear system, 020303 mechanical engineering & transports, 0203 mechanical engineering, [SPI.MECA.MEMA]Engineering Sciences [physics]/Mechanics [physics.med-ph]/Mechanics of materials [physics.class-ph], Ceramics and Composites, Mécanique des matériaux, Sandwich structures, 0210 nano-technology, business, Failure mode map, Failure mode and effects analysis, Sandwich-structured composite, Potting, Civil and Structural Engineering
Abstract: International audience; Inserts of sandwich panel joints are commonly sized using analytical approaches that provide a rough estimationof the pull-out strength. In this investigation, the use of failure mode maps is proposed as an alternative to theconventional methods. These failure charts are created by means of several advanced nonlinear numerical simulationsthat can provide accurate pull-out strength estimations. This technique may require a considerableinvestment of time and effort but, in exchange, it could reduce the time and cost of insert design in the long term.
Published: 2020
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32. Numerical analysis of shear stiffness of an entangled cross-linked fibrous material

Author: Dominique Poquillon, Guilhem Michon, Christophe Bouvet, Fadhel Chatti, Centre National de la Recherche Scientifique - CNRS (FRANCE), Ecole nationale supérieure des Mines d'Albi-Carmaux - IMT Mines Albi (FRANCE), Institut National Polytechnique de Toulouse - Toulouse INP (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 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), Centre interuniversitaire de recherche et d'ingenierie des matériaux (CIRIMAT), Centre National de la Recherche Scientifique (CNRS)-Université Toulouse III - Paul Sabatier (UT3), Université Fédérale Toulouse Midi-Pyrénées-Université Fédérale Toulouse Midi-Pyrénées-Institut National Polytechnique (Toulouse) (Toulouse INP), Université Fédérale Toulouse Midi-Pyrénées-Institut de Chimie du CNRS (INC), 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), Université Toulouse III - Paul Sabatier (UT3), Université de Toulouse (UT)-Université de Toulouse (UT)-Institut de Chimie du CNRS (INC)-Centre National de la Recherche Scientifique (CNRS)-Institut National Polytechnique (Toulouse) (Toulouse INP), Université de Toulouse (UT), and Institut National Polytechnique de Toulouse - INPT (FRANCE)
Subjects: musculoskeletal diseases, Entangled cross-linked fibres, Materials science, Modulus, 02 engineering and technology, 0203 mechanical engineering, [SPI.MECA.MEMA]Engineering Sciences [physics]/Mechanics [physics.med-ph]/Mechanics of materials [physics.class-ph], medicine, General Materials Science, Composite material, Applied Mathematics, Mechanical Engineering, technology, industry, and agriculture, Stiffness, Epoxy, 021001 nanoscience & nanotechnology, Condensed Matter Physics, Finite element method, 020303 mechanical engineering & transports, Shear (geology), Mechanics of Materials, Modeling and Simulation, Joint stiffness, visual_art, Volume fraction, Representative elementary volume, visual_art.visual_art_medium, Mécanique des matériaux, medicine.symptom, 0210 nano-technology, Finite element model, Shear stiffness
Abstract: International audience; The objective of this paper is to understand and study the effect of morphological parameters on the shear stiffness of an entangled cross-linked fibrous material made with carbon fibres where some of the contacts are bonded by the epoxy resin. This current work presents a 3D finite element model using ABAQUS/Standard in order to characterize the mechanical behaviour of different carbon fibre networks rigidified by epoxy cross-links. Numerical simulations are achieved on a representative volume element (RVE) with the orientation distribution of the fibres based on a tested sample. Since not all the strands are perfectly separated, an equivalent diameter of fibre is determined to obtain the rigidity experimen- tally measured in shear. Then, an investigation of the influence of morphological descriptors, such as the distance between cross-links, distribution fibre orientations and junction properties, is carried out. For the entangled cross-linked fibrous material with a small fibre volume fraction, the relationship between the shear stiffness and the fibre volume fraction is a linear function whereas the relation between the shear stiffness and the distance between junctions is a power law with exponent of −3/2. The shear stiff- ness depends slightly on the twisting joint stiffness, and its relationship with the tension joint stiffness is a logarithmic function. The effect of fibre stiffness is also investigated by taking Young’s modulus values corresponding to those of glass fibres, inox fibres or aramid fibres. A linear function is obtained between the shear stiffness and the Young’s modulus. These results are consistent with the analytical models in the literature for a cross-linked fibrous material.
Published: 2020
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33. Inverse approach for flax yarns mechanical properties identification from statistical mechanical characterization of the fabric

Author: Marwa Abida, Ahmad Baklouti, Christophe Bouvet, Florian Gehring, Alexandre Vivet, Centre de recherche sur les Ions, les MAtériaux et la Photonique (CIMAP - UMR 6252), Université de Caen Normandie (UNICAEN), Normandie Université (NU)-Normandie Université (NU)-École Nationale Supérieure d'Ingénieurs de Caen (ENSICAEN), Normandie Université (NU)-Commissariat à l'énergie atomique et aux énergies alternatives (CEA)-Centre National de la Recherche Scientifique (CNRS), 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), Normandie Université (NU)-Commissariat à l'énergie atomique et aux énergies alternatives (CEA)-Centre National de la Recherche Scientifique (CNRS)-Institut de Recherche sur les Matériaux Avancés (IRMA), Normandie Université (NU)-Commissariat à l'énergie atomique et aux énergies alternatives (CEA)-Université de Rouen Normandie (UNIROUEN), Normandie Université (NU)-Institut national des sciences appliquées Rouen Normandie (INSA Rouen Normandie), Institut National des Sciences Appliquées (INSA)-Normandie Université (NU)-Institut National des Sciences Appliquées (INSA)-Centre National de la Recherche Scientifique (CNRS)-Commissariat à l'énergie atomique et aux énergies alternatives (CEA)-Université de Rouen Normandie (UNIROUEN), Institut National des Sciences Appliquées (INSA)-Normandie Université (NU)-Institut National des Sciences Appliquées (INSA)-Centre National de la Recherche Scientifique (CNRS), 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), Commissariat à l'Energie Atomique et aux énergies alternatives - CEA (FRANCE), Centre National de la Recherche Scientifique - CNRS (FRANCE), Institut Supérieur de l'Aéronautique et de l'Espace - ISAE-SUPAERO (FRANCE), and Normandie Université (FRANCE)
Subjects: Fabric, Materials science, Inverse, Modulus, Multi-objective algorithm, Mechanical properties, 02 engineering and technology, Standard deviation, Autre, 0203 mechanical engineering, Ultimate tensile strength, [SPI.MECA.MEMA]Engineering Sciences [physics]/Mechanics [physics.med-ph]/Mechanics of materials [physics.class-ph], General Materials Science, Multiscale modeling, Fiber, Composite material, Instrumentation, Statistical properties, Yarns, Numerical analysis, Vegetal fibers, Yarn, 021001 nanoscience & nanotechnology, 020303 mechanical engineering & transports, Mechanics of Materials, visual_art, visual_art.visual_art_medium, 0210 nano-technology
Abstract: International audience; Plant fiber properties, such as morphological and mechanical, are characterized by a large dispersion. Thereby, a statistical analysis is needed to obtain consistent results. An experimental study, conducted on 50 flax yarns, shows that the flax yarn properties (Young's modulus, tensile strength and diameter) follow Gaussian distributions. This approach is obviously reliable, however time-consuming, to get relevant information. An alternative could be the identification of the yarn mechanical properties using an inverse approach, based on tensile tests conducted on flax fabric reinforcement. The aim of this study is to develop a numerical method that allows to identify the statistical distributions of flax yarn properties based on tensile tests conducted on fabric specimens. The proposed strategy relies on two assumptions. On the one hand, fabric is constituted of several yarns acting like springs in parallel. On the other hand, yarns are considered as brittle-elastic materials. Hence, a yarn breaks when the load reaches its failure strength, leading to a loading redistribution to the intact yarns. A comparison of the numerical and experimental results of flax fabric tensile behavior, and of the flax property statistical distributions allows to confirm the performance of this strategy. The results show that the flax fabric tensile behavior is correctly described by the proposed modeling strategy. The average and the standard deviation of the Young's modulus, the tensile strength and the diameter of flax yarns identified from fabric tensile tests via inverse approach are close to those obtained experimentally on individual yarns. Indeed, the measured average diameter of unitary yarns are 244.4 ± 19.2 μm and the fitted one is 2474.8 ± 17.4 μm, the fitting failure strength 292.3 ± 33.4 MPa are close to the experimental 271.2 ± 47.5 MPa. The identified Young’s modulus is 9.4 ± 0.9 GPa is lower than the experimental 10.8 ± 1.3 GPa
Published: 2020
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34. Combined loadings after medium velocity impact on large CFRP laminate plates: Tests and enhanced computation/testing dialogue

Author: Samuel Rivallant, Guillaume Pichon, Antoine Trellu, Joël Serra, Bruno Castanié, Christophe Bouvet, Léon Ratsifandrihana, 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), SEGULA Technologies [Trappes], Segula Technologies [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), Segula Technologies (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, Scale (ratio), Impact behavior, Computation, Composite number, General Engineering, Test rig, Damage tolerance, 02 engineering and technology, 010402 general chemistry, 021001 nanoscience & nanotechnology, Compression (physics), 01 natural sciences, 0104 chemical sciences, Shear (sheet metal), Laminates, [SPI.MECA.MEMA]Engineering Sciences [physics]/Mechanics [physics.med-ph]/Mechanics of materials [physics.class-ph], Ceramics and Composites, Mécanique des matériaux, Composite material, 0210 nano-technology, Pyramid (geometry)
Abstract: International audience; The development and certification of aeronautical composite structures is still largely based on the pyramid of tests. This approach is extremely costly in terms of number of tests, especially at the level of coupons. Moreover, these tests are highly conservative, under uniaxial loading, and do not represent the actual behavior at structure scale. To overcome these drawbacks, a new methodology has been developed at the Institut Clément Ader, which uses a complex loading test rig for technological specimens. This research focuses on the combined loading after impact of CFRP plates and highlights a specific behavior quite different from the usual CAI (Compression After Impact) response at the scale of coupons. In particular, compression, shear and combined shear/compression loadings were applied to large Carbon Fiber Reinforced Plastics (CFRP) laminated plates and the interaction of the impact damage with the post-buckling behavior has been investigated.
Published: 2020
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35. Damage Mechanics Modelling of the shear nonlinear behavior of Nomex honeycomb core. Application to sandwich beams

Author: Juan de Dios Rodriguez-Ramirez, Christophe Bouvet, Bruno Castanié, 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), 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: Honeycomb, Materials science, General Mathematics, 02 engineering and technology, Sandwich structures -Sandwich testing, 0203 mechanical engineering, Damage mechanics, [SPI.MECA.MEMA]Engineering Sciences [physics]/Mechanics [physics.med-ph]/Mechanics of materials [physics.class-ph], General Materials Science, Sandwich structures, Shear buckling, Civil and Structural Engineering, business.industry, Mechanical Engineering, Sandwich testing, Honeycomb (geometry), Structural engineering, 021001 nanoscience & nanotechnology, Compression (physics), Core (optical fiber), Shear (sheet metal), Nonlinear system, Honeycomb structure, 020303 mechanical engineering & transports, Buckling, Mechanics of Materials, Mécanique des matériaux, 0210 nano-technology, business
Abstract: International audience; In this work, a modelling strategy based on damage mechanics is presented for Nomex honeycomb core. The proposed approach is based on the experimental analysis presented by the authors in [1] and consists of the decoupled modelling of the buckling and collapse of cells for the HRH-78 Nomex honeycomb core with two damage parameters. The proposed approach shows good agreementwith the experimental tests. The computational cost is low, proving the efficacy of this technique. This strategy may avoid using full 3D models that mimic the real shape and is a step toward a full compression/shear nonlinear model forhoneycomb core.
Published: 2020
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36. Effects of dynamics and trigger on energy absorption of composite tubes during axial crushing

Author: Samuel Rivallant, Christophe Bouvet, Jean-François Ferrero, Olivier Dorival, J.-E. Chambe, 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 Catholique d'Arts et Métiers (ICAM), 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 Catholique des Arts et Métiers - ICAM (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, Mechanical Engineering, Energy dissipation, Composite number, Dynamics (mechanics), 020101 civil engineering, Transportation, 02 engineering and technology, Mechanics, Specific energy absorption, Aeronautics, Dissipation, Crash, Industrial and Manufacturing Engineering, 0201 civil engineering, 020303 mechanical engineering & transports, 0203 mechanical engineering, Energy absorption, [SPI.MECA.MEMA]Engineering Sciences [physics]/Mechanics [physics.med-ph]/Mechanics of materials [physics.class-ph], Dynamic crushing, Composite tubes, Mécanique des matériaux
Abstract: International audience; The purpose of this study is to complete a previous quasi-static experimental campaign on the energy absorption performance of composite tubes with the influence of the dynamic effect. Various hybrid composite tubes, involving unidirectional and braided plies with various materials and stacking sequences, were tested both in quasi-static and in dynamic crushing in order to identify their behavior and determine their absorbing capabilities using the Specific Energy Absorption. In dynamic loading, 90°-oriented fibers stabilised by woven plies showed good performances, contrary to static loading, since the energy absorption of the unidirectional laminate oriented at 0° drops by 50% in dynamics.
Published: 2020
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37. On the potting failure of inserts for sandwich panels: Review of defects and experimental analysis

Author: Bruno Castanié, Christophe Bouvet, Juan de Dios Rodriguez-Ramirez, 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: Materials science, Syntactic foam, Mechanical Engineering, General Mathematics, technology, industry, and agriculture, food and beverages, 02 engineering and technology, [SPI.MECA.MSMECA]Engineering Sciences [physics]/Mechanics [physics.med-ph]/Materials and structures in mechanics [physics.class-ph], 021001 nanoscience & nanotechnology, Potting, 020303 mechanical engineering & transports, 0203 mechanical engineering, Mechanics of Materials, General Materials Science, Composite material, 0210 nano-technology, Sandwich-structured composite, Civil and Structural Engineering
Abstract: International audience; In this paper the potting failures of inserts in sandwich structure is analyzed. The case of inserts potted with syntactic foam is investigated. First, a discussion about the influence of defects is made. Then, an experimental campaign is performed to determine the traction and compression behavior of the syntactic foam. Later, a specific technological pull-out test was performed, while a DIC system was used to record the tests. This allowed to observe and understand the different potting failure modes of inserts for sandwich panels. The obtained results suggest that the potting failure of inserts is predominant when fabrication or installation defects are present.
Published: 2020
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38. Validation and modeling of aeronautical composite structures subjected to combined loadings: The VERTEX project. Part 1: Experimental setup, FE-DIC instrumentation and procedures

Author: Bruno Castanié, Jean-Charles Passieux, Jean-Emmanuel Pierré, Joël Serra, Jean-Noël Périé, Christophe Bouvet, 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), 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: Structural testing, Digital image correlation, Engineering, Specific test, Finite Element-Stereo Digital Image Correlation, Composite number, 02 engineering and technology, [SPI]Engineering Sciences [physics], Autre, 0203 mechanical engineering, Virtual test, Boundary value problem, Finite Element-Stereo Digital Image, Civil and Structural Engineering, Composite structures, Multiaxial loading, business.industry, Finite element approach, Isotropy, Internal pressure, Structural engineering, 021001 nanoscience & nanotechnology, Correlation, 020303 mechanical engineering & transports, Ceramics and Composites, 0210 nano-technology, business
Abstract: International audience; The development and certification of aeronautical composite structures is still largely based on the pyramid of tests. This approach is extremely costly in terms of number of tests and design loops. Moreover, it is based on uniaxial tests whereas the real structures are mostly subjected to combined loadings. The aim of the collaborative research program “VERTEX” is to progress towards Predictive Virtual Testing and to significantly reduce the development costs of aeronautical and space programs. In this first part, the specific methodology for multiaxial tests of aeronautical structures is presented. The concept of the technological specimen and its size are justified. Then, the development of a specific test rig is presented, on which compression/tension, shear, internal pressure and combinations are possible. Since structural tests are complex to instrument, a specific full-field measurement technique is developed. It is based on a multi-camera instrumentation and an original Finite Element approach to Stereo Digital Image Correlation (FE-SDIC). Within such a framework, given that the very same mesh can be used for the simulation and the measurement, the corresponding displacements can be compared directly. In addition, a mechanical regularization of the FE-SDIC measurements allows mechanically consistent fields to be evaluated, such as displacement and rotation fields that could be used as boundary conditions in the simulations. The experimental procedure, the measurement methodologies and the calculation/test dialogue are validated on isotropic metal plates in this paper.
Published: 2017
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39. Experimental and numerical analysis of unfolding failure of L-shaped CFRP specimens

Author: Léon Ratsifandrihana, Christophe Bouvet, Pierre Journoud, Bruno Castanié, Frédéric Laurin, 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), Segula Technologies [France], DMAS, ONERA, Université Paris Saclay (COmUE) [Châtillon], ONERA-Université Paris Saclay (COmUE), 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), 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), Office National d'Etudes et Recherches Aérospatiales - ONERA (FRANCE), Université Toulouse III - Paul Sabatier - UT3 (FRANCE), Segula Technologies (FRANCE), and Département de Mécanique des Structures et Matériaux - DMSM (Toulouse, France)
Subjects: Materials science, UNFOLDING FAILURE, Stacking, 02 engineering and technology, Curvature, COMPOSITE L-ANGLE, [SPI]Engineering Sciences [physics], 0203 mechanical engineering, Translaminar matrix cracking, Ultimate tensile strength, Perpendicular, [CHIM]Chemical Sciences, Civil and Structural Engineering, Shearing (physics), TRANSLAMINAR MATRIX CRACKING, [PHYS]Physics [physics], Unfolding failure, business.industry, Numerical analysis, DELAMINATION, Structural engineering, 021001 nanoscience & nanotechnology, Composite L-angle, Transverse plane, 020303 mechanical engineering & transports, Delamination, Ceramics and Composites, Bending moment, Mécanique des matériaux, 0210 nano-technology, business
Abstract: International audience; Highly curved laminated parts are used at the junction between two different perpendicular panels on aircraft primary structures. Usually, these laminates fail by delamination due to a bending moment, which appears when the part is loaded. The bending moment tries to flatten the part and out-of-plane tensile stresses are generated in the curvature. This failure is traditionally called unfolding failure. The modelling strategy called the 'Discrete Ply Model' (DPM) is used to simulate four-point bending tests on L-angle specimens. Experimental results of four point bending tests carried out at ONERA are used to validate the approach. Four different stacking sequences with the same thickness are taken into consideration in this study. In a second part, a sensitivity analysis on frictional coefficient, intralaminar matrix cracking, transverse tensile and shearing strength, and critical energy release rate in modes I and II is performed numerically and provides an original explanation of the failure scenario and the most influential parameter.
Published: 2019
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40. Large damage tolerance analysis with the VERTEX multiaxial test rig

Author: Joël Serra, christophe bouvet, Bruno Castanié, 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), 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.MECA.STRU]Engineering Sciences [physics]/Mechanics [physics.med-ph]/Structural mechanics [physics.class-ph], ComputingMilieux_MISCELLANEOUS
Abstract: International audience
Published: 2019

41. Energy absorption capacity of composite thin-wall circular tubes under axial crushing with different trigger initiations

Author: Jean-François Ferrero, Olivier Dorival, Christophe Bouvet, J.-E. Chambe, 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), Institut Catholique d'Arts et Métiers (ICAM), 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 Catholique des Arts et Métiers - ICAM (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, Matériaux, Composite number, 02 engineering and technology, Specific energy absorption, Aeronautics, [SPI.MECA.MSMECA]Engineering Sciences [physics]/Mechanics [physics.med-ph]/Materials and structures in mechanics [physics.class-ph], 0203 mechanical engineering, Energy absorption, Thin wall, [SPI.MECA.MEMA]Engineering Sciences [physics]/Mechanics [physics.med-ph]/Mechanics of materials [physics.class-ph], Materials Chemistry, Composite tubes, Composite material, Specific Energy Absorption, Crushing, Mechanical Engineering, Energy dissipation, Dissipation, 021001 nanoscience & nanotechnology, [SPI.MECA.GEME]Engineering Sciences [physics]/Mechanics [physics.med-ph]/Mechanical engineering [physics.class-ph], 020303 mechanical engineering & transports, Mechanics of Materials, [SPI.MECA.STRU]Engineering Sciences [physics]/Mechanics [physics.med-ph]/Structural mechanics [physics.class-ph], Ceramics and Composites, 0210 nano-technology, Energy (signal processing)
Abstract: The purpose of this study is to evaluate and compare the ability of various composite structures to dissipate the energy generated during a crash. To this end, circular composite tubes were tested in compression in order to identify their behavior and determine their absorbing capabilities using the specific energy absorption (energy absorbed per unit weight). Several composite tubular structures with different materials and architectures were tested, including hybrid composition of carbon–aramid and hybrid configuration of 0/90 UD with woven or braided fabric. Several inventive and experimental trigger systems have been tested to try and enhance the absorption capabilities of the tested structures. Specific energy absorption values up to 140 kJ.kg−1 were obtained, achieving better than most instances from the literature, reaching around 80 kJ.kg−1. Specimens with 0°-oriented fibers coincidental with the direction of compression reached the highest specific energy absorption values while those with no fiber oriented in this direction performed poorly. Moreover, it has consequently been established that in quasi-static loading, a unidirectional laminate oriented at 0° and stabilized by woven plies strongly meets the expectations in terms of energy dissipation. Incidentally, an inner constrained containment is more effective in most cases, reducing the initial peak load without drastically reducing the specific energy absorption value.
Published: 2019
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42. Experimental investigation of compression and compression after impact of wood-based sandwich structures

Author: Arthur Cantarel, Emmanuel De Luycker, John Susainathan, Florent Eyma, Bruno Castanié, Christophe Bouvet, 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), Laboratoire Génie de Production (LGP), Ecole Nationale d'Ingénieurs de Tarbes, 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 d'Ingénieurs de Tarbes (ENIT), Institut National Polytechnique (Toulouse) (Toulouse INP), Université de Toulouse (UT)-Université de Toulouse (UT)-Institut National Polytechnique (Toulouse) (Toulouse INP), Université de Toulouse (UT)-Université de Toulouse (UT), Centre National de la Recherche Scientifique - CNRS (FRANCE), Ecole nationale supérieure des Mines d'Albi-Carmaux - IMT Mines Albi (FRANCE), Institut National Polytechnique de Toulouse - INPT (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 Institut National Polytechnique de Toulouse - Toulouse INP (FRANCE)
Subjects: Materials science, Matériaux, Composite number, Residual stiffness, chemistry.chemical_element, Compression After Impact, 02 engineering and technology, [SPI.MECA.MSMECA]Engineering Sciences [physics]/Mechanics [physics.med-ph]/Materials and structures in mechanics [physics.class-ph], [SPI.MAT]Engineering Sciences [physics]/Materials, Specific strength, 0203 mechanical engineering, Aluminium, Composite material, Civil and Structural Engineering, 021001 nanoscience & nanotechnology, Compression (physics), Wood, [SPI.MECA.GEME]Engineering Sciences [physics]/Mechanics [physics.med-ph]/Mechanical engineering [physics.class-ph], Core (optical fiber), Residual strength, 020303 mechanical engineering & transports, Impact, Damage, chemistry, Ceramics and Composites, Impact energy, Sandwich, 0210 nano-technology
Abstract: International audience; This paper presents an experimental investigation of compression on pristine specimens and the compression after impact (CAI) response of wood-based sandwich structures. Nine different types of sandwiches, made with plywood core and different aluminum or composite (carbon or glass or flax fiber) skins, are studied. Impact energy levels were fixed at 5 J, 10 J and 15 J in order to create significant defects. Failure modes and damage scenarios are analyzed. The influence of different skins with plywood core is explained in terms of residual strength, residual stiffness, and specific properties. It is shown that this type of structure exhibits very interesting compression properties in terms of specific strength, which is superior to a reference sandwich used for aircraft flooring, and in terms of behavior, with large plateau areas that can be useful for crash issues.
Published: 2019
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43. Insert sizing of sandwich panels by means of a failure mode map

Author: Juan de Dios Rodriguez-Ramirez, Bruno Castanié, christophe bouvet, 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: Honeycomb, [PHYS.MECA.MEMA]Physics [physics]/Mechanics [physics]/Mechanics of materials [physics.class-ph], Shear testing, Syntactic polymer foam, Inserts, Buckling
Abstract: International audience; Sandwich structures are widely used in many industrial applications like acclimated transportation, aeronautics, aerospace, naval, civil engineering, fluid storage, electronics, etc. These structures offer an exceptional benefit when they are used in aeronautics, the incorporation of this technology into the aircraft structures has proved to be a great solution for mass reduction problems due to their important bending stiffness and low weight, which allows to design lightweight parts.Nevertheless, sandwich panels are only used for secondary structures of airplanes, like gear doors or control surfaces. The reason is because their design is complex (against impacts or loads introductions for instance) and difficult to ensure the quality requirements.In this context, sandwich panels joints through inserts is a problem that is still investigated today and is the main subject of this research.The insert sizing is usually made using the methods proposed in the “Insert design handbook” of the ESA [1] and the “Military handbook 23A” [2]. These analytical methods based in the research carried by Ericksen in 1953 could lead to important errors of the pull-out allowable load prediction for some cases [3].This research is about the study of an insert installed into a sandwich panel for aeronautical applications with Nomex honeycomb core and CFRP skins. The objective is to develop a model of the insert behavior (including the different failure mechanisms) when it is pulled out.This includes a detailed study of the Nomex honeycomb core shear damage behavior [4], and a modelling strategy that allows to incorporate the nonlinear shear behavior at a very low computational cost [5]. Also, a study of the breaking of the potting is made to better understand this failure mode of inserts. Then, a F.E. model of the insert is developed and validated by comparison against experimental results showing good agreement Finally, this F.E. model it is used extensively to perform virtual tests and to trace an insert failure mode maps that allows to estimate the insert pull-out strength as function of the properties of the inserts, like size and their material properties.
Published: 2019

44. Simulation of medium velocity impact and compression or shear after impact on large composite laminated plates

Author: Antoine Trellu, christophe bouvet, Samuel Rivallant, Léon Ratsifandrihana, Alexandre Chardonneau, Institut Supérieur de l'Aéronautique et de l'Espace (ISAE-SUPAERO), SEGULA Technologies [Trappes], Segula Technologies [France], and École Nationale Supérieure d'Arts et Métiers (ENSAM) - Bordeaux
Subjects: Medium velocity impact, Large composite plates, Impact moyenne vitesse, Numerical modelling, Grandes plaques composites, Modélisation numérique, [PHYS.MECA.MSMECA]Physics [physics]/Mechanics [physics]/Materials and structures in mechanics [physics.class-ph], [INFO.INFO-MO]Computer Science [cs]/Modeling and Simulation, [SPI.MAT]Engineering Sciences [physics]/Materials
Abstract: International audience; Composites are known to be vulnerable to out-of-plane loading such as impact. To design composite structures without performing long and costly experimental campaigns several numerical approaches have been developed. The model developed in Institut Clément Ader over the last year enables representation of main failures appearing in a composite laminate subjected to low velocity/low energy impact. The work presented here deals with the validation of this model to account for damages in composite laminates under medium velocity impact.; Les matériaux composites sont connus pour être vulnérables aux sollicitations hors plan comme les impacts. Pour s'abstenir de réaliser des campagnes expérimentales couteuses, de nombreux outils de simulations numériques sont développés. Le modèle développé à l'Institut Clément Ader depuis une dizaine d'années permet de représenter les principaux endommagements présents dans un stratifié composite lors d'un impact à faible vitesse/faible énergie. Le travail présenté ici a pour but de valider le bon fonctionnement du modèle pour des impacts à moyenne vitesse.
Published: 2019

45. High temperature translaminar fracture in tension and in compression of woven-ply thermoplastic laminates

Author: Juan Daniel Pujols Gonzalez, Benoît Vieille, christophe bouvet, Groupe de physique des matériaux (GPM), Centre National de la Recherche Scientifique (CNRS)-Institut national des sciences appliquées Rouen Normandie (INSA Rouen Normandie), Institut National des Sciences Appliquées (INSA)-Normandie Université (NU)-Institut National des Sciences Appliquées (INSA)-Normandie Université (NU)-Université de Rouen Normandie (UNIROUEN), Normandie Université (NU), 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), École Nationale Supérieure d'Arts et Métiers (ENSAM) - Bordeaux, Université de Rouen Normandie (UNIROUEN), Normandie Université (NU)-Normandie Université (NU)-Institut national des sciences appliquées Rouen Normandie (INSA Rouen Normandie), Institut National des Sciences Appliquées (INSA)-Normandie Université (NU)-Institut National des Sciences Appliquées (INSA)-Centre National de la Recherche Scientifique (CNRS)-Institut de Recherche sur les Matériaux Avancés (IRMA), Université de Caen Normandie (UNICAEN), Normandie Université (NU)-Normandie Université (NU)-École Nationale Supérieure d'Ingénieurs de Caen (ENSICAEN), Normandie Université (NU)-Commissariat à l'énergie atomique et aux énergies alternatives (CEA)-Université de Rouen Normandie (UNIROUEN), Normandie Université (NU)-Institut national des sciences appliquées Rouen Normandie (INSA Rouen Normandie), Institut National des Sciences Appliquées (INSA)-Normandie Université (NU)-Institut National des Sciences Appliquées (INSA)-Centre National de la Recherche Scientifique (CNRS)-Université de Caen Normandie (UNICAEN), Normandie Université (NU)-École Nationale Supérieure d'Ingénieurs de Caen (ENSICAEN), Normandie Université (NU)-Commissariat à l'énergie atomique et aux énergies alternatives (CEA)-Centre National de la Recherche Scientifique (CNRS), 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: high temperature, woven-ply laminate, Digital Image Correlation, translaminar fracture, thermoplastique, [SPI.MECA.MSMECA]Engineering Sciences [physics]/Mechanics [physics.med-ph]/Materials and structures in mechanics [physics.class-ph], thermoplastic, haute température, rupture translaminaire, stratifiétissé, corrélation d’images numériques
Abstract: International audience; The translaminar fracture behavior of three composite laminates, based on thermoplastic matrix PEEK reinforcedby a woven carbon fibers obtained by consolidation process, has been studied by means of Compact Tension (CT) and Compact Compression (CC) tests.An orthotropic laminate and two quasi-isotropic laminates, have been tested at room temperature (RT) and at 150°C (i.e.for a temperature slightly higher than the glass transition temperature, Tg), with the purpose of evaluation the influence of the stacking sequence and the temperature on the damage mechanisms.The CT type tests show that the temperature influence on the overall mechanical response remains low. In contrast, the CT type tests reveal a diminution in the mechanical resistance and an augmentation in the global ductile behavior.By means of the 2D Digital Image Correlation and the implementation of a algorithm based on the sigma indicator (confidence interval in the area of interest), the crack propagation was measured during loading, then the G-R curves have been obtained from the compliance method; Le comportement en rupture translaminaire de trois composites stratifiés, à matrice thermoplastique PEEK renforcée par un tissu de fibres de carbone obtenus par thermo-compression, a été étudié au moyen d’essais Compact Tension (CT) et Compact Compression (CC). Un stratifié orthotrope et deux stratifiés quasi-isotropes ont été testés à température ambiante (TA) et à 150°C (i.e. pour une température légèrement plus élevée que la température de transition vitreuse, Tg), afin d’évaluer l’influence de la séquence d’empilement et de la température sur les mécanismes d’endommagement.Les essais de type CT montrent que l’influence de la température sur la réponse mécanique globale reste faible. Au contraire,lesessaisde typeCC révèlent une diminution de la résistance mécanique et une augmentation du comportement ductile global.Avec la mise en œuvre d’une technique de corrélation d’images numériques2Det l’implémentation d’un algorithme basé sur l’indicateur sigma (intervalle de confiance dans la zone d’intérêt), la propagation de la fissure a été mesuréelors de chargement, puis les courbes G-R ont été obtenues à partir de la méthode de la compliance.
Published: 2019

46. Etude numérique de la propagation de fissure dans un composite tissé

Author: Pierre Journoud, christophe bouvet, Samuel Rivallant, Nicolas Dubary, Léon Ratsifandrihana, 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), SEGULA Technologies [Trappes], Segula Technologies [France], and École Nationale Supérieure d'Arts et Métiers (ENSAM) - Bordeaux
Subjects: numerical simulation, rupture de fibres, propagation de fissure translaminaire, stratifié tissé, simulation numérique, [SPI.MECA.MSMECA]Engineering Sciences [physics]/Mechanics [physics.med-ph]/Materials and structures in mechanics [physics.class-ph], fiber failure, translaminar crack propagation, woven laminate
Abstract: International audience; Thanks to their low mass and high performances, composites drawan increasing interest in many fields, such as aeronautics. Nevertheless, composites structures are particularly vulnerable to out-of-plane solicitations.Research [1-3] have shown differences between woven and unidirectional composites. Woven composites have better damage tolerances thanks to textile architecture and mechanisms of effort diffusion [4]. Moreover, they have better properties on out-of-plan solicitations and a greater dissipative power than unidirectional composites.Woven composites have shown a particular interest for aeronautical manufacturers, yet their breaking mechanisms remain complex.This study is focused on failure mechanisms of woven composite. We used the numerical model which has developed at the Institute Clement Ader over the last years called Discrete Ply Model (DPM), with the aim of simulating tensile tests on notched and unnotched specimens of woven composites. The objective is to study translaminar crack growth propagations and improve the understanding of failure mechanism. We take into consideration the critical energy release rate of the fiber failure in mode I and II, the shearing plasticity and the effect of weaving point.; Grâce à leurs faibles masses et leurs hautes propriétés mécaniques, les composites sont des matériaux de plus en plus utilisés dans de nombreux domaines,notamment dans l’aéronautique. Néanmoins, les structures composites sont particulièrement vulnérables vis-à-vis des sollicitations hors plan.Les recherches [1-3] ont montré des différences significatives entre composites unidirectionnels et tissés. Grâce à leurs architectures et aux mécanismes de diffusion des efforts,les tissés possèdent de meilleures propriétés en sollicitation hors plan que les unidirectionnels[4]. Ils présentent donc un intérêt non négligeable pour les constructeurs aéronautiques;cependant leurs mécanismes de rupture restent complexes.Dans ce travail nous nous proposons d’étudier les mécanismes de ruptures des composites tissés.Pour cela nous avons utilisé le modèle numérique développé à l’Institut Clément Ader depuis une dizaine d’années, le Discrete Ply Model (DPM), afin de simuler des essais de traction sur éprouvettes tissées avec et sans pré-entaille. Le but est d’étudier la propagation de fissures translaminaires et d’améliorer la compréhension des mécanismes d’endommagements. Nous nous sommes notamment intéressés à la prise en compte du taux de restitution d’énergie critique en rupture de fibres en mode I et II, à la plasticité en cisaillement ainsi qu’à l’effet des points de tissages.
Published: 2019

47. Fracture mechanics of hybrid composites with ductile matrix and brittle fibers: Influence of temperature and constraint effect

Author: Benoit Vieille, Juan-Daniel Pujols Gonzalez, Christophe Bouvet, 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 National des Sciences Appliquées de Rouen - INSA (FRANCE), Institut Supérieur de l'Aéronautique et de l'Espace - ISAE-SUPAERO (FRANCE), Université Toulouse III - Paul Sabatier - UT3 (FRANCE), Normandie Université (FRANCE), Groupe de physique des matériaux (GPM), Centre National de la Recherche Scientifique (CNRS)-Institut national des sciences appliquées Rouen Normandie (INSA Rouen Normandie), Institut National des Sciences Appliquées (INSA)-Normandie Université (NU)-Institut National des Sciences Appliquées (INSA)-Normandie Université (NU)-Université de Rouen Normandie (UNIROUEN), Normandie Université (NU), 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)-Institut National des Sciences Appliquées (INSA)-Université Toulouse III - Paul Sabatier (UT3), Université Fédérale Toulouse Midi-Pyrénées-Université Fédérale Toulouse Midi-Pyrénées-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), Université de Rouen Normandie (UNIROUEN), Normandie Université (NU)-Normandie Université (NU)-Institut national des sciences appliquées Rouen Normandie (INSA Rouen Normandie), Institut National des Sciences Appliquées (INSA)-Normandie Université (NU)-Institut National des Sciences Appliquées (INSA)-Centre National de la Recherche Scientifique (CNRS)-Institut de Recherche sur les Matériaux Avancés (IRMA), Université de Caen Normandie (UNICAEN), Normandie Université (NU)-Normandie Université (NU)-École Nationale Supérieure d'Ingénieurs de Caen (ENSICAEN), Normandie Université (NU)-Commissariat à l'énergie atomique et aux énergies alternatives (CEA)-Université de Rouen Normandie (UNIROUEN), Normandie Université (NU)-Institut national des sciences appliquées Rouen Normandie (INSA Rouen Normandie), Institut National des Sciences Appliquées (INSA)-Normandie Université (NU)-Institut National des Sciences Appliquées (INSA)-Centre National de la Recherche Scientifique (CNRS)-Université de Caen Normandie (UNICAEN), Normandie Université (NU)-École Nationale Supérieure d'Ingénieurs de Caen (ENSICAEN), Normandie Université (NU)-Commissariat à l'énergie atomique et aux énergies alternatives (CEA)-Centre National de la Recherche Scientifique (CNRS), 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), and Université de Toulouse (UT)-Centre National de la Recherche Scientifique (CNRS)-IMT École nationale supérieure des Mines d'Albi-Carmaux (IMT Mines Albi)
Subjects: Toughness, Materials science, 02 engineering and technology, Polyether ether ketone, chemistry.chemical_compound, Brittleness, Fracture toughness, 0203 mechanical engineering, Ultimate tensile strength, [SPI.MECA.MEMA]Engineering Sciences [physics]/Mechanics [physics.med-ph]/Mechanics of materials [physics.class-ph], Materials Chemistry, Fracture mechanics, Thermoplastic, Composite material, Tensile testing, Strain energy release rate, Mechanical Engineering, Mechanical testing, R-curves, 021001 nanoscience & nanotechnology, High temperature, 020303 mechanical engineering & transports, chemistry, Mechanics of Materials, Ceramics and Composites, Mécanique des matériaux, 0210 nano-technology
Abstract: The fracture behavior of hybrid carbon and glass fiber woven-ply reinforced polyether ether ketone thermoplastic quasi-isotropic laminates is investigated. Single-edge-notch bending and single-edge-notch tensile tests were conducted at room temperature and at a temperature higher than the glass transition temperature ( Tg) to study the influence of both the constraint effect and the temperature on the strain energy release rate in laminates with ductile polyether ether ketone matrix and brittle fibers. As failure is primarily driven by fibers breakage in tension (single-edge-notch tensile test) and in tension/compression (single-edge-notch bending), it turns out that a temperature increase has very little influence on the mode I critical translaminar fracture toughness KIc though the ductility of polyether ether ketone matrix is exacerbated at T > Tg. It also appears that the constraint effect has very little influence on KIc as single-edge-notch tensile test and single-edge-notch bending specimens have virtually the same mean value (about 45MPa. [Formula: see text]). Single-edge-notch bending specimens being characterized by a gradual failure, the G-R curves were derived from the computation of the compliance loss and the corresponding gradual crack growth in agreement with the ASTM standard E1820. From the evolution of the G-R curves at high temperature, the highly ductile behavior of the polyether ether ketone matrix at T > Tg provides a good intrinsic toughness to the material, and the bridging of translaminar crack by the glass fibers at the outer surfaces of laminates contribute to a moderate increase in its extrinsic toughness.
Published: 2019
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48. Prediction of the ultimate strength of quasi-isotropic TP-based laminates structures from tensile and compressive fracture toughness at high temperature

Author: Benoit Vieille, Juan-Daniel Pujols Gonzalez, Christophe Bouvet, 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 National des Sciences Appliquées de Rouen - INSA (FRANCE), Institut Supérieur de l'Aéronautique et de l'Espace - ISAE-SUPAERO (FRANCE), Université Toulouse III - Paul Sabatier - UT3 (FRANCE), Normandie Université (FRANCE), Groupe de physique des matériaux (GPM), Université de Rouen Normandie (UNIROUEN), Normandie Université (NU)-Normandie Université (NU)-Institut national des sciences appliquées Rouen Normandie (INSA Rouen Normandie), Institut National des Sciences Appliquées (INSA)-Normandie Université (NU)-Institut National des Sciences Appliquées (INSA)-Centre National de la Recherche Scientifique (CNRS)-Institut de Recherche sur les Matériaux Avancés (IRMA), Université de Caen Normandie (UNICAEN), Normandie Université (NU)-Normandie Université (NU)-École Nationale Supérieure d'Ingénieurs de Caen (ENSICAEN), Normandie Université (NU)-Commissariat à l'énergie atomique et aux énergies alternatives (CEA)-Université de Rouen Normandie (UNIROUEN), Normandie Université (NU)-Institut national des sciences appliquées Rouen Normandie (INSA Rouen Normandie), Institut National des Sciences Appliquées (INSA)-Normandie Université (NU)-Institut National des Sciences Appliquées (INSA)-Centre National de la Recherche Scientifique (CNRS)-Université de Caen Normandie (UNICAEN), Normandie Université (NU)-École Nationale Supérieure d'Ingénieurs de Caen (ENSICAEN), Normandie Université (NU)-Commissariat à l'énergie atomique et aux énergies alternatives (CEA)-Centre National de la Recherche Scientifique (CNRS), 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), Centre National de la Recherche Scientifique (CNRS)-Institut national des sciences appliquées Rouen Normandie (INSA Rouen Normandie), Institut National des Sciences Appliquées (INSA)-Normandie Université (NU)-Institut National des Sciences Appliquées (INSA)-Normandie Université (NU)-Université de Rouen Normandie (UNIROUEN), Normandie Université (NU), 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, Glass fiber, Failure, 02 engineering and technology, Bending, High-temperature, 010402 general chemistry, 01 natural sciences, Industrial and Manufacturing Engineering, Fracture toughness, Ultimate tensile strength, [SPI.MECA.MEMA]Engineering Sciences [physics]/Mechanics [physics.med-ph]/Mechanics of materials [physics.class-ph], Fracture mechanics, Thermoplastic, Composite material, Tension (physics), Microbuckling, Mechanical Engineering, Composite laminates, 021001 nanoscience & nanotechnology, Compression (physics), 0104 chemical sciences, Mechanics of Materials, Ceramics and Composites, Mécanique des matériaux, 0210 nano-technology
Abstract: International audience; This paper is intended to test the capacity of a simple model based on fracture mechanics concepts to predict the ultimate strength of notched hybrid carbon and glass fibers woven-ply reinforced PolyEther Ether Ketone (PEEK) thermoplastic (TP) quasi-isotropic (QI) laminates under different temperature conditions. In such materials, translaminar failure is the primary failure mode driven by the breakage of 0° and 45° oriented fibers in tension as well as the formation of kink-band in compression. Single-Edge-Notched Bending (SENB), Open-Hole-Tensile (OHT) and Open-Hole-Compression (OHC) specimens have been conducted at room temperature (RT) and at a temperature higher than the glass transition temperature (Tg). The Critical Damage Growth model derived from the Average Stress Criterion and Linear Elastic Fracture Mechanics (LEFM) have been applied to open-hole specimens to determine the critical damage zone from which the fracture toughness in tension (0° and 45° fibers breakage) KIc-tension and in compression (kink-band formation) KIc_comp. are estimated. In Single Edge Notched Bending (SENB) specimens experience simultaneous tension/compression. From the estimation of KIc-tension and KIc_comp., the ultimate strength of SENB specimens can be predicted. LEFM equations combined with the critical fracture toughness in tension give relatively accurate results, suggesting that failure is driven by fibers bundles breakage in tension.
Published: 2019
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49. Experimental analysis of impact and post-impact behaviour of inserts in Carbon sandwich structures

Author: Bruno Castanié, Jean-Paul Giavarini, Laurent Mezeix, Natthawat Hongkarnjanakul, Simon Dols, Christophe Bouvet, 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), Burapha University (THAILAND), Geo-Informatics and Space Technology Development Agency - GISTDA (THAILAND), Sogeclair (FRANCE), Département de Mécanique des Structures et Matériaux - DMSM (Toulouse, France), Faculty of Informatics, Burapha University, 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), SOGECLAIR (FRANCE), Geo-Informatics and Space Technology Development Agency (GISTDA), Centre interuniversitaire de recherche et d'ingenierie des matériaux ( CIRIMAT ), Institut National Polytechnique [Toulouse] ( INP ) -Université Toulouse III - Paul Sabatier ( UPS ), Université Fédérale Toulouse Midi-Pyrénées-Université Fédérale Toulouse Midi-Pyrénées-Centre National de la Recherche Scientifique ( CNRS ), Institut Clément Ader ( ICA ), Institut Supérieur de l'Aéronautique et de l'Espace ( ISAE-SUPAERO ) -IMT École nationale supérieure des Mines d'Albi-Carmaux ( IMT Mines Albi ) -Université Toulouse III - Paul Sabatier ( UPS ), Université Fédérale Toulouse Midi-Pyrénées-Université Fédérale Toulouse Midi-Pyrénées-Centre National de la Recherche Scientifique ( CNRS ) -Institut National des Sciences Appliquées - Toulouse ( INSA Toulouse ), Institut National des Sciences Appliquées ( INSA ) -Institut National des Sciences Appliquées ( INSA ), 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, [ SPI.MAT ] Engineering Sciences [physics]/Materials, 02 engineering and technology, Impact test, Insert, 0203 mechanical engineering, Autre, Honeycomb, Composite material, Landing gear, Insert (composites), business.industry, Mechanical Engineering, Structural engineering, Carbon Laminates, [ SPI.MECA.MSMECA ] Engineering Sciences [physics]/Mechanics [physics.med-ph]/Materials and structures in mechanics [physics.class-ph], 021001 nanoscience & nanotechnology, Compression (physics), Residual strength, 020303 mechanical engineering & transports, Impact, Mechanics of Materials, Pull-through, Ceramics and Composites, Sandwich, 0210 nano-technology, business
Abstract: International audience; In aeronautics, honeycomb sandwich structures are widely used for secondary structures such as landing gear doors, flaps or floors, and for primary structures in helicopters or business jets. These structures are generally joined by using local reinforcements of the insert type. In the present study, 50 J low velocity impact tests were performed on inserts using a drop-weight device and the impact response and failure patterns were analysed. Impacted specimens were then pull-through tested to 2 failure. Some of the tests were stopped before final failure in order to obtain precise details on the failure scenario. It was shown that, in the cases studied, the residual strength after impact was very high (about 90%) in comparison to the large reductions habitually observed in Compression After Impact tests.
Published: 2019
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50. Surface integrity while trimming of composite structures: X-ray tomography analysis

Author: Christophe Bouvet, Redouane Zitoune, N. Nguyen-Dinh, S. Leroux, 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), Thai Nguyen University of Technology, 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), ACTIA (FRANCE), Thai Nguyen University of Technology (VIETNAM), 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, Scanning electron microscope, Composite number, Crater volume, 02 engineering and technology, 021001 nanoscience & nanotechnology, [SPI.MECA.GEME]Engineering Sciences [physics]/Mechanics [physics.med-ph]/Mechanical engineering [physics.class-ph], Machining temperature, 020303 mechanical engineering & transports, 0203 mechanical engineering, Machining, Ceramics and Composites, Surface roughness, Trimming, Tomography, Mécanique des matériaux, Tool wear, Composite material, 0210 nano-technology, Trimming CFRP, X-ray tomography, Civil and Structural Engineering, Surface integrity
Abstract: International audience; The aim of this paper is to study the influence of the process parameters (cutting speed and feed) of the conventional trimming on cutting forces, machining temperatures, tool wear and machining quality of Carbon Fibers Reinforced Plastics (CFRP) using PCD tool. The machining quality was characterized using three different techniques such as Scanning Electron Microscopy (SEM), 3D optical topography and X-ray tomography. The originality of this work is based mainly on the multi-scale characterization of the machined surfaces. In fact, a new parameter based on the measurement of the volume of craters is proposed and compared to the surface roughness criterion (Sa) and the X-ray tomography images. The obtained results show that, with the crater volume criterion as well as the X-ray tomography images, the effect of the machining parameters and the wear of the tool on the textured surfaces are well correlated to surface roughness criterion (Sa). In addition, it was observed that the feed speed and tool wear were the major factors affecting the cutting forces and the machining temperatures.
Published: 2019
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