Search

Your search keyword '"Elixir Aircraft"' showing total 3 results
Start Over Author "Elixir Aircraft" Topic wrinkling
3 results on '"Elixir Aircraft"'

1. 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
Full Text
View/download PDF

2. Local buckling on large sandwich panels applied to light aviation: Experimental and computation dialogue

Author

M. Ginot, C. Bouvet, B. Castanié, M. D'Ottavio, J. Serra, N. Mahuet, 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 Nanterre (UPN), and Elixir Aircraft

Subjects
Structural testing, Experimental, [SPI]Engineering Sciences [physics], Mechanics of Materials, Applied Mathematics, Mechanical Engineering, Modeling and Simulation, General Materials Science, Sandwich structures, Condensed Matter Physics, Wrinkling, Sandwich structures Local buckling Wrinkling Structural testing Experimental, Local buckling
Abstract

International audience; Wrinkling is a local buckling phenomenon in sandwich structures subjected to compression and shear loading that is challenging for the aircraft design engineer. Numerous wrinkling models are proposed in the literature but historical formulas developed after the Second World War are still widely used by the industry with important knock down factors. Theoryexperiment correlation should be the final step in validating and evaluating the models. This article presents an experimental-computational dialogue on structural tests on large sandwich panels of dimensions 558 x 536 mm 2 representative of the design used in light aviation. The panels were subjected to compressive and shear loading by using the VERTEX test bench and wrinkling failures were observed. Comparisons are first made with linear

Published
2023
Full Text
View/download PDF

3. Experimental setup and failure scenarios

Author

Ginot, M., Bouvet, C., Castanié, Bruno, Serra, Joël, Mahuet, N., Elixir Aircraft, 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
Structural testing, [SPI.MECA.MSMECA]Engineering Sciences [physics]/Mechanics [physics.med-ph]/Materials and structures in mechanics [physics.class-ph], Sandwich structures, Wrinkling, Light aviation, Local buckling
Abstract

International audience; The design of light aircraft sandwich structures is driven by a local buckling phenomenon named “wrinkling” which can be the primary cause of failure of such structures. Structural tests using the VERTEX methodology were performed to access the wrinkling behaviour of 558x536 mm2 technological sandwich specimens representative of the design used in light aviation. The operating principle of the VERTEX machine is the use of four hydraulic actuators to load a rectangular box structure, the upper part of the central box being closed by the sandwich under test. Thus, sandwich specimens were tested under compressive and shear loading. A wrinkling scenario was identified thanks to Stereo Digital Image Correlation and a high-speed camera. Wrinkling localisation is driven by mechanical and geometrical aspects. Experiments on wrinkling in sandwich panels remain rare in the literature at this level of the test pyramid for certification of aeronautical structures. This upper scale presents some advantages as it allows multiaxial loading and boundary conditions consistent with a lightweight aeronautical structure. Technological elements can also be added to study their influence on the structure. The result will lead to interesting future investigations on the dialogue between experiments and models in a forthcoming paper.

Published
2023
Full Text
View/download PDF

Catalog

Books, media, physical & digital resources
See catalog results