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131 results on '"Bruno Castanié"'

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. The GAP methodology: A new way to design composite structures

Author: Florian Neveu, Bruno Castanié, and Philippe Olivier
Subjects: Materials of engineering and construction. Mechanics of materials, TA401-492
Abstract: With the growing demand for composite parts, more and more designs or re-designs are required to use such materials. This paper presents a new methodology for designing composite structures by considering three essential variables: the geometry, the architecture and the manufacturing process. The methodology proves to be useful during the pre-design phase of the project, when important decisions have to be taken regarding the choice of the manufacturing route and the investments needed. The methodology starts from the design (the geometry of which relies on the designer's creativity) and then gives clear insight into the possibilities offered by the concepts from a composite point of view. These include the types of architecture and technologies that are compatible as well as the manufacturing processes. The GAP methodology (Geometry, Architecture, Process) is intended to provide an efficient way to start a composite project by giving a broad overview of the possibilities and by reducing the risks of poor decisions at the very beginning of the project. In this article, innovative composite structure design issues will be presented before the methodology itself is explained. Two generic case studies are then presented to illustrate how the GAP methodology works. Keywords: Design methodology, Composite materials, Manufacturing processes, Conceptual design
Published: 2019
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5. The effect of rectification of composite materials on the mechanical behavior of long fiber composite materials

Author: Redouane Zitoune, Florent Eym, Bruno Castanié, and Madjid Haddad
Subjects: carbon fibers, thermoplastic resine, defects, strength, mechanical testing, Materials of engineering and construction. Mechanics of materials, TA401-492
Abstract: This paper focuses on the study of the effect of rectification by grinding on the mechanical behavior in quasi-static tests (compression and inter-laminar shear) of two long fiber composite materials machined by two cutting processes: tool machining (edge cutting) and abrasive diamond cutting (ADS). Two sets of specimens of different surface roughness are generated by varying the cutting conditions for each material. One set is rectified. First, the results of compression and inter laminar shear tests show that the mechanical behavior is highly affected by the surface roughness. Secondly it is shown that the operation of rectification improves the mechanical behavior. However this improvement is highly affected by the surface roughness of the specimen before rectification and is dependent on the long fiber composite material.
Published: 2016
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6. 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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7. Dynamic crushing of wood-based sandwich composite tubes

Author: Bruno Castanié, Florent Eyma, Romain Guélou, Arthur Cantarel, 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), 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: Materials science, General Mathematics, Dynamic, Composite number, Glass fiber, chemistry.chemical_element, Core (manufacturing), [SPI.MECA.MSMECA]Engineering Sciences [physics]/Mechanics [physics.med-ph]/Materials and structures in mechanics [physics.class-ph], 02 engineering and technology, 0203 mechanical engineering, Tube, Energy absorption, General Materials Science, Composite material, Tube (container), Composites, Civil and Structural Engineering, Crushing, Mechanical Engineering, Epoxy, 021001 nanoscience & nanotechnology, Mécanique des structures, 020303 mechanical engineering & transports, chemistry, Mechanics of Materials, visual_art, visual_art.visual_art_medium, Sandwich, Wood veneers, 0210 nano-technology, Carbon, Poplar
Abstract: International audience; The paper presents the results of dynamic crushing of sandwich tubes that had skins made of carbon or glass fibres-with epoxy resin-and an I214 poplar ply core. By increasing the number of poplar plies from two to six, the absorbed energy is doubled, showing the significant contribution of the wood. The Specific Energy Absorption of sandwiches with carbon fibre skins oscillated between 49.4 and 60 J/g while that with glass fibre skins varied from 35.4 to 43.3 J/g.
Published: 2021
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8. 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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9. Static crushing of wood based sandwich composite tubes

Author: Samuel Rivallant, Romain Guélou, Florent Eyma, Arthur Cantarel, 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: Materials science, Static compression, Glass fiber, Composite number, 0211 other engineering and technologies, 02 engineering and technology, Epoxy, [SPI.MECA.MSMECA]Engineering Sciences [physics]/Mechanics [physics.med-ph]/Materials and structures in mechanics [physics.class-ph], 01 natural sciences, 010101 applied mathematics, Core (optical fiber), Coupling effect, Energy absorption, visual_art, 021105 building & construction, Ceramics and Composites, visual_art.visual_art_medium, Transportation industry, 0101 mathematics, Composite material, ComputingMilieux_MISCELLANEOUS, Civil and Structural Engineering
Abstract: This study presents static compression of sandwich tubes for crash applications in the transportation industry. The tubes were made from “I214” poplar veneers for the core, and carbon or glass woven plies reinforced with epoxy resin composites for the skins. The number of I214 layers in the core was varied between 2 and 6 while keeping the same number of plies for the skins. The results reveal interesting energy absorption performance of such structures in static, together with a coupling effect. In comparison with reference, all-carbon tubes, the sandwich tubes with carbon fibre skins having six I214 poplar plies showed an increase in mass of 75.2 g (+271%), a slightly degraded Specific Energy Absorption (- 7.2 J / g, − 10%), and an increase in the energy absorbed (+3,017 J, + 242%). For sandwich tubes with glass fibre skins having six I214 poplar plies, the SEA improved (+16 J / g, + 75%), the energy absorbed increased by 2,192 J (+602%) and the mass increased by 75.3 g (+314%). The SEA levels obtained were of the order of 61.2 J / g for sandwich tubes with carbon fibres and 32.5 J / g for those made of glass fibres (average values from static tests on all configurations).
Published: 2021
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10. 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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11. 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

12. 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

13. 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

14. Processing and Application of Engineering Materials

Author: Bruno Castanie, Ramesh K. Agarwal, Sandip A. Kale, Shanmugam Thillikkani, Bruno Castanie, Ramesh K. Agarwal, Sandip A. Kale, and Shanmugam Thillikkani
Subjects: Building materials, Chemical engineering, Chemistry, Engineering, Physics
Abstract: Special topic volume with invited peer-reviewed papers only
Published: 2024

15. The 2nd Eco-Materials Conference in Africa (CEMA)

Author: Abdellatif Imad, Vincent Sambou, Salam Sawadogo, Bruno Castanie, Abdellatif Imad, Vincent Sambou, Salam Sawadogo, and Bruno Castanie
Subjects: Building materials, Chemical engineering, Chemistry, Engineering, Physics
Abstract: Selected peer-reviewed extended articles based on abstracts presented at the 2nd Eco-Materials Conference in Africa (CEMA)Aggregated Book
Published: 2024

16. Advanced Materials and Materials Application

Author: Femiana Gapsari, Bruno Castanie, Ramesh K. Agarwal, Femiana Gapsari, Bruno Castanie, and Ramesh K. Agarwal
Subjects: Building materials, Chemical engineering, Chemistry, Engineering, Mechanical engineering, Physics
Abstract: Special topic volume with invited peer-reviewed papers only
Published: 2024

17. Crashworthiness of poplar wood veneer tubes

Author: Samuel Rivallant, Florent Eyma, Bruno Castanié, Arthur Cantarel, Romain Guélou, 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, Crushing, Wood veneer, Mechanical Engineering, Stacking, Aerospace Engineering, 020101 civil engineering, Ocean Engineering, 02 engineering and technology, Wood, 0201 civil engineering, 020303 mechanical engineering & transports, 0203 mechanical engineering, Mechanics of Materials, Energy absorption, Automotive Engineering, [SPI.MECA.MEMA]Engineering Sciences [physics]/Mechanics [physics.med-ph]/Mechanics of materials [physics.class-ph], Crashworthiness, Dynamic 7 8, Composite material, Safety, Risk, Reliability and Quality, Static, Poplar, Civil and Structural Engineering
Abstract: International audience; This work studies the potential of using wooden tubes for crash applications. The tubes were made from 1 mm thick "I214" poplar veneers, according to different stacking sequences. Four configurations were characterized under static crushing (5 mm/min) and the one that performed best ([90/04/90]) was chosen to undergo dynamic tests under a drop weight tower (5.7 m/s). This configuration presents significant energy absorption performance in static (31.6 J / g) and in dynamic (28.5 J / g) crushing for a material that is natural, ecological (low carbon footprint), recyclable, and low cost in comparison with other materials such as composite materials. As with composites, the position, number, and orientation of the plies directly affect the amount of energy absorbed. The use of poplar, one of the weakest woods in mechanical terms, shows the possibilities of wood for this use.
Published: 2021
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18. Experimental study and in-situ FBG monitoring of process-induced strains during autoclave co-curing, co-bonding and secondary bonding of composite laminates

Author: Bruno Castanié, Gérard Bernhart, Philippe Olivier, Laure Moretti, 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: In situ, Cure behaviour, Materials science, Composite number, Assembly, Thermosetting polymer, 02 engineering and technology, Composite laminates, 010402 general chemistry, 021001 nanoscience & nanotechnology, 01 natural sciences, 0104 chemical sciences, law.invention, [SPI]Engineering Sciences [physics], Optical microscope, Mechanics of Materials, law, Thermosetting resin, Process monitoring, Ceramics and Composites, Adhesive, Composite material, 0210 nano-technology, Curing (chemistry), Secondary bonding
Abstract: International audience; The geometric stability of bonded structural parts, such as self-stiffened panels, is a critical issue in aeronautics. However, autoclave curing and bonding of large complex integrated primary structures often induce distortions compromising their geometric stability. Composite cure-induced strains and distortions have been extensively studied in the literature but the influence of the adhesive on these distortions has often been overlooked. More experimental data are therefore necessary to properly understand its influence on process-induced strains and its behaviour during cure. The present paper reports a wide range of new experimental investigations showing the non-negligible influence of the adhesive on cure-induced distortions of composite assemblies. The experimental data presented include post-cure distortion measurements, optical microscope imaging, micro-tomography imaging and FBG in-situ strain monitoring during an autoclave bonding process. These experiments demonstrate the impact of the adhesive film behaviour and of the manufacturing bonding process on final distortions and strains of composite assemblies.
Published: 2021
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19. Effect of milled notches on the strength of open hole, filled holes, single and double lap shear CFRP tension coupons

Author: Bruno Castanié, Victor Achard, Clement Chirol, 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: Machining process, Materials science, 02 engineering and technology, 021001 nanoscience & nanotechnology, Residual strength, 020303 mechanical engineering & transports, 0203 mechanical engineering, Shear (geology), Ultimate tensile strength, [SPI.MECA.MEMA]Engineering Sciences [physics]/Mechanics [physics.med-ph]/Mechanics of materials [physics.class-ph], Ceramics and Composites, Composite material, 0210 nano-technology, Open hole, Failure mode and effects analysis, Civil and Structural Engineering
Abstract: Splitting is the presence of a long, thin matrix crack observed in laminates stacked with unidirectional plies. The importance of splitting has been highlighted several times in the literature to explain failure scenarios of open and, more rarely, filled hole CFRP coupon specimens. This failure mode also seems to play an important role in the increase of residual strength after fatigue that is sometimes observed in such specimens. In this study, a machining process is used to mill notches at the boundary of holes for open and filled holes, and for single and double lap shear specimens. These notches mimics the effects of splitting and a significant increase of the quasi-static tensile strength (up to + 20%) is observed in open/ filled hole coupons and for double lap shear specimens. However, for single lap-shear specimens, the results are within the dispersion of the experimental results or lower.
Published: 2020
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20. Review of composite sandwich structure in aeronautic applications

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, 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), Elixir Aircraft (FRANCE), Département de Mécanique des Structures et Matériaux - DMSM (Toulouse, France), Institut National des Sciences Appliquées - Toulouse (INSA Toulouse), Institut National des Sciences Appliquées (INSA)-Institut National des Sciences Appliquées (INSA)-Centre National de la Recherche Scientifique (CNRS)-Université Toulouse III - Paul Sabatier (UT3), Université Fédérale Toulouse Midi-Pyrénées-Université Fédérale Toulouse Midi-Pyrénées-IMT École nationale supérieure des Mines d'Albi-Carmaux (IMT Mines Albi), and Institut Mines-Télécom [Paris] (IMT)-Institut Mines-Télécom [Paris] (IMT)-Institut Supérieur de l'Aéronautique et de l'Espace (ISAE-SUPAERO)
Subjects: Structure (mathematical logic), Engineering, business.industry, Mechanical Engineering, ComputerApplications_COMPUTERSINOTHERSYSTEMS, Composite, 02 engineering and technology, Aeronautic, 021001 nanoscience & nanotechnology, Construction engineering, 020303 mechanical engineering & transports, 0203 mechanical engineering, Mechanics of Materials, [SPI.MECA.MEMA]Engineering Sciences [physics]/Mechanics [physics.med-ph]/Mechanics of materials [physics.class-ph], Ceramics and Composites, Structure design, TA401-492, Mécanique des matériaux, Sandwich structures, 0210 nano-technology, business, Materials of engineering and construction. Mechanics of materials
Abstract: International audience; 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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21. Effective Static and Dynamic Finite Element Modeling of a Double Swept Composite Rotor Blade

Author: Erasmo Carrera, Bruno Castanié, Enrico Zappino, Matteo Filippi, 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: Materials science, Blade (geometry), Rotor (electric), business.industry, Composite number, 020101 civil engineering, 02 engineering and technology, Structural engineering, [SPI.MECA.MSMECA]Engineering Sciences [physics]/Mechanics [physics.med-ph]/Materials and structures in mechanics [physics.class-ph], 021001 nanoscience & nanotechnology, Finite element method, 0201 civil engineering, law.invention, law, 0210 nano-technology, business, ComputingMilieux_MISCELLANEOUS
Abstract: The paper concerns mechanical responses of helicopter blades made of composite materials. Structures with complicated geometries are modeled by using both beam and solid finite elements. The adopted one-dimensional kinematics only encompasses pure displacements; therefore, the connection with three-dimensional elements can be carried out with ease. Contributions to elastic and inertial matrices deriving from nodes shared by beams and solids are merely summed together through a standard assembling procedure. Stress, free vibration, and time response analyses have been performed on different configurations. A straight metallic rotating structure and a swept-tip blade made of an orthotropic material have been considered for verification and validation purposes. Current results have been compared with experimental data and numerical solutions available in the literature. Furthermore, a straight and a double-swept blade with a realistic airfoil have been studied. For the straight configuration, the one-dimensional results have been compared with finite element solutions obtained with commercial software. The methodology enabled complicated stress distributions and coupling phenomena to be predicted with reasonable accuracy and affordable computational efforts.
Published: 2020
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22. 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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23. Manufacturing and quasi-static bending behavior of wood-based sandwich structures

Author: John Susainathan, Emmanuel De Luycker, Bruno Castanié, Arthur Cantarel, Florent Eyma, 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 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, Composite number, Failure, Core (manufacturing), 02 engineering and technology, Bending, 7. Clean energy, 0203 mechanical engineering, Flexural strength, Sandwich structures, Composite material, Sandwich-structured composite, Civil and Structural Engineering, business.industry, Mechanical testing, Structural engineering, Fibre-reinforced plastic, 021001 nanoscience & nanotechnology, Wood, Molding (decorative), Mécanique des structures, 020303 mechanical engineering & transports, [SPI.MECA.STRU]Engineering Sciences [physics]/Mechanics [physics.med-ph]/Structural mechanics [physics.class-ph], Ceramics and Composites, 0210 nano-technology, business, Quasistatic process
Abstract: International audience; The quasi-static behavior of innovative wood based sandwich structures with plywood core and skins made either of aluminum or of fiber reinforced polymer (carbon, glass or flax composite skins) was investigated. The wood based sandwich structures were subjected to three point static bending tests to determine their strength and failure mechanisms. Two different manufacturing processes, namely vacuum bag molding and thermo-compression, were used to manufacture the structures. The influence of some aspects of the different manufacturing processes on the flexural behavior of wood based sandwich structures are discussed. It is shown that manufacturing processes influence strongly the static responses. Failure modes and strengths are investigated during quasi-static bending tests. Bending tests showed that the mechanical characteristics were very high compared to those of a reference sandwich that is currently used for civil aircraft floors. This new kind of structure is environmentally friendly and very cheap, and seems promising for the transportation industry in general.
Published: 2017
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24. 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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25. Characterization and modelling of cure-dependent properties and strains during composites manufacturing

Author: Philippe Olivier, Gérard Bernhart, Laure Moretti, 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: thermosetting resin, Materials science, Mechanical Engineering, Aeronautical industry, Composite number, Thermosetting polymer, 02 engineering and technology, 010402 general chemistry, 021001 nanoscience & nanotechnology, process simulation, 01 natural sciences, 0104 chemical sciences, cure behaviour, Autoclave, [SPI]Engineering Sciences [physics], Mechanics of Materials, Geometric stability, Materials Chemistry, Ceramics and Composites, Composite material, 0210 nano-technology, Curing (chemistry)
Abstract: International audience; The geometric stability of structural parts is a critical issue in the aeronautical industry. However, autoclave curing of primary structural composite parts may cause significant distortions and divergences between the mould nominal geometries and the final shapes of the parts. To be able to anticipate such distortions, a robust simulation tool is needed, which can be implemented only if the phenomena involved are properly understood and characterized. The thermo-kinetic behaviour of the M21EV/IMA prepreg is fully characterized in this paper. Thermal strains and chemical shrinkages are measured using Thermo-Mechanical Analysis during the cure and the experimental method developed allows the thermo-chemical strains to be obtained even during the early stages of the cure. An experimental setup is developed to measure the thermo-mechanical behaviour of the material during its cure. Thanks to these measurements, a new constitutive mechanical model, inspired from the CHILE model, is defined. These data are then used as inputs for an FEA simulation of the entire curing process. Finally, the model is validated using the cure degree, glass transition and temperature monitoring, and post-cure distortion measurements.
Published: 2020
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26. 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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27. 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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28. 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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29. Implementation of a Simulation Tool of Strains Induced During the Co-bonding of Autoclave-cured Parts

Author: Bruno Castanié, Léonard Serrano, Laure Moretti, Philippe Olivier, Gérard Bernhart, 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, Manufacturing process, Experimental deformation, Composite number, Material behaviour, Bonded composites, Commercial software, Deformation, Stringers, [SPI]Engineering Sciences [physics], Structural adhesive, Stringer, Adhesives, Autoclave (industrial), Curing, Experimental work, Adhesive, Steel beams and girders, Composite material, Deformation (engineering), Thermomechanical behaviour, Process induced strains
Abstract: International audience; Our on-going research focusses upon composite structural parts such as stiffened panels with co-bonded stringers. This study is aiming to developing a numerical tool based on commercial softwares (e.g. Abaqus ® and Fortran ®) enabling after-cure deformations to be predicted for co-bonded composite parts. Several simulations moduli were developed to describe i the thermochemical, ii the thermomechanical behaviours of prepreg plies and structural adhesive film and iii the mould/part interaction. An experimental work was conducted in parallel in order to get firstly simulation input parameters (i.e. material behaviour laws) and secondly experimental deformations on co-bonded composite specimen. The materials used were the Hexcel U.D. prepreg tape M21EV/IMA and the Cytec FM300M structural adhesive film. During a first step (first cure cycle), the process-induced strains of the laminated panel that will be stiffened with stringers were computed and compared to experimental ones. During the second step (second cure cycle) the process-induced strains and deformation were computed on the cured laminate but also on the stringer foot and on the structural adhesive as shown in Fig. 1. Lastly comparing experimental results to simulations shows clearly the interest of considering a 2 steps manufacturing process with 2 cure cycles instead of a single one in which all the components (i.e. panel, adhesive and stringer foot) are cured together.
Published: 2019
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30. 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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31. 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

32. 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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33. 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

34. Visuo-tactile and topographic characterizations of finished wood surface quality by French consumers and industrials: acceptability thresholds for raised grain

Author: Bruno Castanié, Tahiana Ramananantoandro, Florent Eyma, M. Ramanakoto, ESSA Forêts, Université d'Antananarivo, 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: 0106 biological sciences, Wood machining, media_common.quotation_subject, Varnish, Visuo-tactile analysis, Context (language use), Planing, Surface finish, 010603 evolutionary biology, 01 natural sciences, Topographic parameters, [SPI.MAT]Engineering Sciences [physics]/Materials, Fagus sylvatica, Mining engineering, Quality (business), Beech, media_common, Ecology, biology, Forestry, biology.organism_classification, Sanding, Visuo tactile, visual_art, Waterborne varnish, visual_art.visual_art_medium, Environmental science, Raised grain, 010606 plant biology & botany
Abstract: International audience; Context: Raised grain occurs on wood surfaces after the application of a waterborne varnish and forces manufacturers to sand the surfaces between coats. Actually, little research has characterised this phenomenon and no techniques have been discovered to avoid its occurrence.Aims: This study aims to identify the topographic parameters that explain the visuo-tactile sensation of raised grain and to define a finished surface quality acceptable to consumers and industry.Methods: Oak (Quercus robur L.) and beech (Fagus sylvatica L.) wood surfaces were planed and sanded in order to have various levels of raised grain. Visuo-tactile analyses were carried out on surfaces having received one coat of varnish to characterise raised grain and having two coats to characterise the acceptable finished surface quality without sanding. Topographic parameters were measured on each type of varnished surface and correlated with the visuo-tactile scores.Results: Raised grain was characterised by the visuo-tactile sensation of protruding peaks and a certain amount of material in the core of the roughness profile for both wood species. Industrials overestimated the surface quality required by consumers. Thresholds of topographic parameters were determined to define acceptable finished surface quality.Conclusion: These findings allowed objective criteria to be defined for describing raised grain and to help industries to optimise their wood machining and finishing processes.
Published: 2019
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35. 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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36. Virtual testing of metallic inserts for sandwich structures

Author: Juan de Dios Rodriguez-Ramirez, 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), 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, Inserts, Sandwich, [SPI.MECA.MSMECA]Engineering Sciences [physics]/Mechanics [physics.med-ph]/Materials and structures in mechanics [physics.class-ph], Nomex, FEA, [SPI.MAT]Engineering Sciences [physics]/Materials, [SPI.MECA.GEME]Engineering Sciences [physics]/Mechanics [physics.med-ph]/Mechanical engineering [physics.class-ph]
Abstract: International audience; In this research, the virtual testing approach is used to study the failure of inserts in sandwich structures. First, a reduced F.E. model of inserts is presented, which includes nonlinear aspects of the materials such as the buckling and collapse of the honeycomb cells, the failure of the potting and the matrix failure of the skins. These model are validated through comparison with real tests showing a good agreement. This work is part of the development of an insert sizing method that could be an alternative to the classical analytical methods.
Published: 2018

37. Experimental and numerical analysis of the shear nonlinear behaviour of Nomex honeycomb core: Application to insert sizing

Author: Bruno Castanié, Christophe Bouvet, Juan de Dios Rodriguez-Ramirez, 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 ), IMT École nationale supérieure des Mines d'Albi-Carmaux ( IMT Mines Albi ) -Institut Supérieur de l'Aéronautique et de l'Espace ( ISAE-SUPAERO ) -Université Paul Sabatier - Toulouse 3 ( UPS ) -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 ), Département de Mécanique des Structures et Matériaux ( DMSM ), Institut Supérieur de l'Aéronautique et de l'Espace ( ISAE-SUPAERO ), 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, Shear testing, Materials science, Finite elements, 02 engineering and technology, 0203 mechanical engineering, [SPI.MECA.MEMA]Engineering Sciences [physics]/Mechanics [physics.med-ph]/Mechanics of materials [physics.class-ph], Boundary value problem, Civil and Structural Engineering, Nomex honeycomb, Inserts, business.industry, Buckling, Numerical analysis, Structural engineering, 021001 nanoscience & nanotechnology, Sizing, Finite element method, Nonlinear system, 020303 mechanical engineering & transports, Shear (geology), [ SPI.MECA.MEMA ] Engineering Sciences [physics]/Mechanics [physics.med-ph]/Mechanics of materials [physics.class-ph], Ceramics and Composites, Mécanique des matériaux, 0210 nano-technology, business
Abstract: International audience; This work is a contribution to the understanding of the nonlinear shear behaviour caused by cell postbuckling inNomex honeycomb cores. First, an experimental benchmark study was made of different designs for the sheartesting of honeycomb cores. Then, several test specimens were fabricated and tested, a 3D DIC system being usedto measure and record the displacements. An Artificial Neural Network (ANN) was also used to identify the onsetof bucking and collapse of the cells. The influence of the overall boundary conditions of shear tests on thebuckling of the cells is presented both experimentally and numerically. The reversibility and test procedureresults suggest that it may be possible to allow the shear strength to be increased by up to 35% under certainconditions.
Published: 2018
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38. Continuum Damage Modeling of Shear Postbuckling in Honeycomb Core

Author: Juan de Dios Rodriguez, 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: Condensed Matter::Soft Condensed Matter, [SPI]Engineering Sciences [physics], [SPI.MECA.MSMECA]Engineering Sciences [physics]/Mechanics [physics.med-ph]/Materials and structures in mechanics [physics.class-ph]
Abstract: International audience; Recently, the authors have highlighted by both numerical analysis and experiments the nonlinear behavior under shear of honeycomb [1]. The results showed that the buckling of the Nomex honeycomb core present a nonlinear elastic behavior beyond the buckling point. This is due to a reversible postbuckling as in aerospace structures. Depending on the load direction and the boundaries of the honeycomb the failure scenario is different. In classical tests such as double rail shear tests or double lap shear tests, the main loading direction is orthogonal to the cell edges at the vertex of the hexagonal shape. Thus, after a postbuckling regime, the honeycomb fails by collapse in shear of theses edges. Although for the tested specimen which mimics quite well the inserts in sandwich panels, the loading direction is parallel to this cell edges and the structures takes more easily the shear buckling thus generating a gain in the allowable up to 35 %. These observations allow the authors to propose a two parameters damage model to capture the shear nonlinear behavior of honeycomb cores. The first parameter will represent the initial buckling of the cells and the start of the collapse of the cells, this is from the initiation of the nonlinear behavior until the maximal shear stress. The second will represent the final collapse of the cells, this is from point where the maximal shear stress is reached until the shear stress is zero. Main results are shown below (the upper curve is the comparison with experiments and the two other represents the evolution of the damage parameters.
Published: 2018

39. The effect of rectification of composite materials on the mechanical behavior of long fiber composite materials

Author: Bruno Castanié, Redouane Zitoune, Florent Eym, and Madjid Haddad
Subjects: Materials science, Abrasive, Laminar flow, Grinding, Diamond cutting, Shear (sheet metal), Rectification, Machining, mechanical testing, carbon fibers, lcsh:TA401-492, Surface roughness, lcsh:Materials of engineering and construction. Mechanics of materials, thermoplastic resine, Composite material, strength, defects
Abstract: This paper focuses on the study of the effect of rectification by grinding on the mechanical behavior in quasi-static tests (compression and inter-laminar shear) of two long fiber composite materials machined by two cutting processes: tool machining (edge cutting) and abrasive diamond cutting (ADS). Two sets of specimens of different surface roughness are generated by varying the cutting conditions for each material. One set is rectified. First, the results of compression and inter laminar shear tests show that the mechanical behavior is highly affected by the surface roughness. Secondly it is shown that the operation of rectification improves the mechanical behavior. However this improvement is highly affected by the surface roughness of the specimen before rectification and is dependent on the long fiber composite material.
Published: 2016
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40. A critical review of PV systems’ faults with the relevant detection methods

Author: Khaled Osmani, Ahmad Haddad, Thierry Lemenand, Bruno Castanier, Mohammad Alkhedher, and Mohamad Ramadan
Subjects: PV faults, Fault detection, Detection methods, Fault type, PV troubleshooting, Renewable energy sources, TJ807-830, Agriculture (General), S1-972
Abstract: PhotoVoltaic (PV) systems are often subjected to operational faults which negatively affect their performance. Corresponding to different types and natures, such faults prevent the PV systems from achieving their nominal power output and attaining the required level of energy production. Regarding the operational optimization of PV systems, this paper aims primarily at surveying and categorizing different types of PV faults, classified as electrical, internal, and external, where each is thoroughly investigated: internal faults occur at the PV cellular level, and can either be short circuit, open circuit, bridging, or bypass diode faults. External faults on the other side are mainly classified as temporary (i.e., clouds shading, snowstorms, etc.) or permanent (e.g., glass breakage, frame defects, etc.) mismatch faults. Lastly, electrical faults involve common circuitry problems, such as short circuits (e.g., line to ground, line to line, etc.), power processing units’ faults (e.g., inverter faults), and arc faults. As for the detection methods, six major fault detection methods are investigated for the AC side of the PV system with twenty-nine total AC based fault detection methods. On the other hand, eleven major fault detection methods are surveyed for the DC side of PV systems with seventy-three total DC based fault detection methods. The investigated methods are critically analyzed, and compared relevantly to each other, within the mutual sub-sets. The resulting tabulated comparative data assessments for PV faults (i.e., cause-effect relationships, impact on the PV system performance), as well as for faults detection methods (i.e., priority for application, etc.) compose a rich background for related PV systems’ performance security fields, where a nexus future work is also suggested.
Published: 2023
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41. Experimental investigation of impact behavior of wood-based sandwich structures

Author: Arthur Cantarel, Bruno Castanié, Florent Eyma, John Susainathan, Emmanuel De Luycker, 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), 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), and Université Toulouse III - Paul Sabatier - UT3 (FRANCE)
Subjects: Materials science, 02 engineering and technology, Fiber-reinforced composite, 7. Clean energy, Low energy, 0203 mechanical engineering, 11. Sustainability, [SPI.MECA.MEMA]Engineering Sciences [physics]/Mechanics [physics.med-ph]/Mechanics of materials [physics.class-ph], Composite material, Acoustic insulation, Sandwich-structured composite, business.industry, 021001 nanoscience & nanotechnology, Wood, Renewable energy, 020303 mechanical engineering & transports, Impact, Damage, 13. Climate action, Mechanics of Materials, Ceramics and Composites, Transportation industry, Sandwich, Fire resistance, Mécanique des matériaux, 0210 nano-technology, business
Abstract: International audience; Low carbon emission and sustainable development are shared goals throughout the transportation industry. One way to meet such expectations is to introduce lightweight materials based on renewable sources. Sandwich panels with plywood core and fiber reinforced composite skins appear to be good candidates. Additional properties of wood such as fire resistance or thermal and acoustic insulation are also essential for many ap- plications and could lead to a new interest for this old material. In this paper, Sandwich panels with two different types of plywood and four different skins (aluminum and glass, CFRP, or flax reinforced polymer) are tested under low-velocity/low energy impacts and their behavior is discussed.
Published: 2018
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42. Experimental and numerical analysis of Carbon Fiber Reinforced Polymer notched coupons under tensile loading

Author: Joël Serra, Bruno Castanié, Christophe Bouvet, Caroline Petiot, 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), Airbus Defence and Space [Toulouse], Airbus (FRANCE), Centre National de la Recherche Scientifique - CNRS (FRANCE), Ecole nationale supérieure des Mines d'Albi-Carmaux - IMT Mines Albi (FRANCE), Institut National des Sciences Appliquées de Toulouse - INSA (FRANCE), Institut Supérieur de l'Aéronautique et de l'Espace - ISAE-SUPAERO (FRANCE), Université Toulouse III - Paul Sabatier - UT3 (FRANCE), Département de Mécanique des Structures et Matériaux - DMSM (Toulouse, France), Institut 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, Stacking, Discrete Ply Modeling, 02 engineering and technology, 0203 mechanical engineering, Autre, Ultimate tensile strength, Notched tensile test, Composite material, Civil and Structural Engineering, Stress concentration, Carbon fiber reinforced polymer, business.industry, Numerical analysis, Structural engineering, Epoxy, Composite laminates, 021001 nanoscience & nanotechnology, Finite element method, 020303 mechanical engineering & transports, visual_art, Ceramics and Composites, visual_art.visual_art_medium, Infrared thermography, 0210 nano-technology, business, Experiments, Finite element model
Abstract: International audience; The behavior of composite laminates subject to notch based stress concentrations is difficult to apprehend, especially the mechanisms of damage progression leading to total failure. Numerical and experimental investigations were carried out on three different stacking sequences of notched, thin ply carbon/epoxy laminates. This paper presents a computational study of notched tensile tests (U-notch) using the Discrete Ply Modeling (DPM) method, which has already proved efficient on both in-plane and out-of-plane loading cases, such as pull through, low velocity impact and compression after impact. The specificities of this finite element model are its discrete nature (interface elements to model delamination and matrix cracks), the small number of parameters required, and its robustness. This work follows on from the study of open-hole tensile tests (same three layups) by the same authors [1] and analyzes the influence of layup and notch shape. Comparisons with experiments (using infrared technology) demonstrate that tensile strengths, and failure scenarios and patterns are predicted with acceptable accuracy.
Published: 2017
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43. Validation and modeling of aeronautical composite structures subjected to combined loadings: The VERTEX project. Part 2: Load envelopes for the assessment of panels with large notches

Author: Jean-Emmanuel Pierré, Joël Serra, Bruno Castanié, Jean-Charles Passieux, Christophe Bouvet, Caroline Petiot, Jean-Noël Périé, Airbus (FRANCE), Centre National de la Recherche Scientifique - CNRS (FRANCE), Ecole nationale supérieure des Mines d'Albi-Carmaux - IMT Mines Albi (FRANCE), Institut National des Sciences Appliquées de Toulouse - INSA (FRANCE), Institut Supérieur de l'Aéronautique et de l'Espace - ISAE-SUPAERO (FRANCE), Université Toulouse III - Paul Sabatier - UT3 (FRANCE), Département de Mécanique des Structures et Matériaux - DMSM (Toulouse, France), Institut 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), Airbus Group Innovations [Suresnes], Airbus [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: Engineering, Structural testing, Composite number, Test rig, Failure, 02 engineering and technology, Certification, 0203 mechanical engineering, [SPI.MECA.MEMA]Engineering Sciences [physics]/Mechanics [physics.med-ph]/Mechanics of materials [physics.class-ph], Virtual test, Civil and Structural Engineering, Composite structures, business.industry, Multiaxial loading, Structural engineering, 021001 nanoscience & nanotechnology, Finite element-digital image correlation, 020303 mechanical engineering & transports, Damage, Ceramics and Composites, Mécanique des matériaux, 0210 nano-technology, business, Finite Element-Digital Image Correlation, Model
Abstract: International audience; One of the important issues in the certification of composite aeronautical structures is large notches. In this paper, tests are carried out on technological specimens under tensile, shear and combined loadings using the VERTEX test rig presented in the first part of this publication. Strong interactions between postbuckling and propagation of cuts are observed. The specifically developed FE-SDIC methodology presented allows a first dialog between calculation and testing. The Discrete Ply Modeling method is able to compute the onset of failure in such complex tests. New test responses called “envelope curves” are proposed and are obtained by following a load path that allows the behavior of the notched structure to be validated for certification purposes. This methodology should eventually lead to a new vision of the test pyramid with the help of “Predictive Virtual Testing” procedures.
Published: 2017
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44. Modélisation d'essais structuraux sur plaques entaillées

Author: Joël Serra, Jean-Emmanuel Pierré, Jean-Noël PERIE, Jean-Charles Passieux, 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), École des Ponts ParisTech (ENPC), 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 Clément Ader ( ICA ), IMT École nationale supérieure des Mines d'Albi-Carmaux ( IMT Mines Albi ) -Institut Supérieur de l'Aéronautique et de l'Espace ( ISAE-SUPAERO ) -Université Paul Sabatier - Toulouse 3 ( UPS ) -Institut National des Sciences Appliquées - Toulouse ( INSA Toulouse ), and Institut National des Sciences Appliquées ( INSA ) -Institut National des Sciences Appliquées ( INSA ) -Centre National de la Recherche Scientifique ( CNRS )
Subjects: [ SPI.MAT ] Engineering Sciences [physics]/Materials, ComputingMilieux_MISCELLANEOUS, [SPI.MAT]Engineering Sciences [physics]/Materials
Abstract: International audience
Published: 2017

45. Etude expérimentale et numérique de la propagation de coupure dans des stratifiés composites soumis à de la traction simple

Author: Joël Serra, christophe bouvet, Bruno Castanié, Caroline Petiot, 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), Airbus Group Innovations [Suresnes], Airbus [France], Université Paris-Saclay, 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: Entailles, Thermographie infrarouge, [SPI.MECA.STRU]Engineering Sciences [physics]/Mechanics [physics.med-ph]/Structural mechanics [physics.class-ph], Endommagement, Composite
Abstract: National audience; Les singularités de type coupure dans des structures minces en matériaux stratifiés composites sont particulièrement difficiles à appréhender vis-à-vis de l’endommagement et des mécanismes de rupture. Le comportement de trois séquences d ’empilement contenant le même nombre de plis (avec des modifications dans l’ordre des plis) est étudié à l’aide de la thermographie infrarouge puis simulé à l’aide d’un modèle éléments finis utilisant des interfaces cohésives pour représenter la fissuration matricielle, le délaminage et leurs couplages (« Discrete Ply Model »).
Published: 2017

46. Sur le dialogue essais-calcul dans les essais structuraux complexes

Author: Joël Serra, Jean-Emmanuel Pierré, Jean-Noël PERIE, Jean-Charles Passieux, Christophe Bouvet, Bruno Castanié, 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), Université Paris-Saclay, 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: Grandes coupures, Essais structuraux, [SPI.MECA.STRU]Engineering Sciences [physics]/Mechanics [physics.med-ph]/Structural mechanics [physics.class-ph], Endommagement, Composites
Abstract: National audience; Des essais de structures composites entaillées sous sollicitations combinées sont réalisés sur un banc spécifique développé dans le cadre de l’ANR Vertex. La réponse est d’ordre structural et l’éprouvette est intrinsèque à la structure et interagit avec le banc. Ces essais sont instrumentés par la Stéréo-CIN-EF qui permet de capturer les conditions aux limites sur l’éprouvette lors de l’essai et un échange de données est effectuée avec un modèle avancé d’endommagement des structures composites de type DPM.
Published: 2017

47. Bearing fatigue of composite laminates: Damage monitoring and fatigue life prediction

Author: Emmanuel Mermoz, Laurent Michel, Frédéric Lachaud, Cyril Sola, Arnaud Delabie, Bruno Castanié, 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), Aéroport International de Marseille-Provence (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), Airbus Helicopters, Aeroport International de Marseille-Provence, 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 (INSA)-Institut National des Sciences Appliquées (INSA)-Université Toulouse III - Paul Sabatier (UPS), and 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)
Subjects: Materials science, Composite number, Computed tomography, 02 engineering and technology, Industrial and Manufacturing Engineering, law.invention, [SPI]Engineering Sciences [physics], 0203 mechanical engineering, law, medicine, Displacement (orthopedic surgery), Composite material, Fatigue, Bearing (mechanical), medicine.diagnostic_test, business.industry, Mechanical Engineering, Fabrics/textile, Mechanical testing, Structural engineering, Composite laminates, 021001 nanoscience & nanotechnology, Fatigue limit, Carbon fibre, Mécanique des structures, 020303 mechanical engineering & transports, Mechanics of Materials, [SPI.MECA.STRU]Engineering Sciences [physics]/Mechanics [physics.med-ph]/Structural mechanics [physics.class-ph], Service life, Ceramics and Composites, 0210 nano-technology, business, Vibration fatigue
Abstract: International audience; In hybrid composite/metallic structures, loads can be transmitted from one part to the other through localized contact pressures, i.e., bearing. Such structures may be rotating structures, which can accumulate as many as 109 load cycles during their service life. Designing safe hybrid rotating structures thus requires a sound understanding of how composite joints degrade under bearing fatigue. Pin-bearing fatigue tests were run under load-control. Damage mechanisms were investigated using computed tomography, and the pin displacement was closely monitored thanks to a green-LED micrometer. Building upon the gathered experimental evidences, several damage indicators were then analysed. In particular, hysteresis losses were found to give interesting insights into the fatigue phenomenon, suggesting the existence of a fatigue limit in the very high cycle fatigue (VHCF) regime.
Published: 2017
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48. Analysis of hole wall defects of drilled carbon fiber reinforced polymer laminates

Author: Audrey Benaben, Robert Piquet, Bruno Castanié, Frédéric Lachaud, Soraya Catché, 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), Airbus [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: Carbon fiber reinforced polymer, Materials science, Scanning electron microscope, Composite Laminates, Mechanical Engineering, Composite number, Drilling, Surface finish, Composite laminates, Roughness, [SPI.MECA.GEME]Engineering Sciences [physics]/Mechanics [physics.med-ph]/Mechanical engineering [physics.class-ph], Microscopic observation, Mechanics of Materials, Bearing surface, Materials Chemistry, Ceramics and Composites, Composite material
Abstract: International audience; The hole wall defects created during drilling of carbon fiber reinforced polymer laminates are analyzed. First, an analysis of the location of the defects on the wall is performed. It is shown that, using results of orthogonal cutting, it is possible to predict the location of the main defects. Then refined scanning electron microscopic observation shows the different patterns of the defects. These observations raise the question of the quantification and measurement of the quality of holes drilled in composite laminates. Two roughness parameters, Ra and the bearing surface are compared and significant differences are found. This study is a contribution to a better definition of quality indicators for machined surfaces in composite structures, which should help to limit overquality and production costs.
Published: 2014
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49. Study of trimming damages of CFRP structures in function of the machining processes and their impact on the mechanical behavior

Author: Bruno Castanié, Florent Eyma, Madjid Haddad, Habiba Bougherara, Redouane Zitoune, 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), Ryerson University [Toronto], 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: B. Mechanical properties, Materials science, Cutting tool, B. Delamination, Mechanical Engineering, Abrasive, Diamond, Surface finish, engineering.material, Fatigue limit, Industrial and Manufacturing Engineering, [SPI.MECA.GEME]Engineering Sciences [physics]/Mechanics [physics.med-ph]/Mechanical engineering [physics.class-ph], Shear (sheet metal), Machining, Mechanics of Materials, B. Fatigue, Ceramics and Composites, engineering, Trimming, Composite material, A. Carbon fibers, B. Defects
Abstract: International audience; The main focus of this paper is to investigate the defects generated by different machining processes (namely burr tool machining, abrasive water jet machining \textquoteleftAWJM\textquoteright and abrasive diamond cutter \textquoteleftADS\textquoteright) and their impact on the mechanical behavior of CFRP in quasi-static (compression and inter-laminar shear) and tensile\textendashtensile fatigue tests. The cutting conditions are selected so that different levels of degradation can be obtained. The machined surface is characterized using roughness measuring devices with and without contact and SEM observations. The results show that the defects generated during the trimming process with a cutting tool are fibers pull-out and resin degradation. These defects are mainly located in the layers with the fibers oriented at -45° and 90°. However, when using abrasive water jet and abrasive diamond processes, the defects generated have the form of streaks and are not dependent on the fiber orientation. Furthermore, the results of quasi-static tests performed on specimens machined by cutting tools show that AWJ specimens offer a better resistance in compression but the ADS samples offer higher inter-laminar-shear strengths. Moreover, the results of fatigue tests show that specimens machined with a burr tool offer higher endurance limit. Finally, it is concluded that the type and the mode of the mechanical loading (quasi-static fatigue) affect the mechanical response of CFRP and favor a given machining process.
Published: 2014
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50. Perçage d’un matériau composite tissé 3D. Influence des conditions d’usinage et de l’usure de l’outil sur les efforts de coupe et la qualité d’usinage

Author: Mathias Sève, Redouane Zitoune, Nicolas Cadorin, 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: [PHYS.MECA.MEMA]Physics [physics]/Mechanics [physics]/Mechanics of materials [physics.class-ph], Materials science, Machining, Drill, Cutting force, Composite number, Lubrication, Drilling, A diamond, General Materials Science, Tool wear, Composite material
Abstract: International audience; An experimental study was lead in order to identify the impact of cutting parameters over the machining quality and cutting forces when drilling an interlock composite 3D woven with a diamond coated drill with lubrication. Two approaches were studied: design of experiments and standardized tool/material method derived from metal machining. For both approaches, feed rate has been identified as the most influent parameter, while cutting speed was not influent. Then wear tests were carried on in order to quantify the impact of cutting parameters over tool wear. Wear tests have proven that tool wear is mainly dependent on the machined length and that it does not impact much the machining quality.
Published: 2013
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