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

Autor: M. Ginot, C. Bouvet, B. Castanié, M. D'Ottavio, J. Serra, N. Mahuet
Přispěvatelé: 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), Elixir Aircraft
Jazyk: angličtina
Rok vydání: 2023
Předmět:
Zdroj: International Journal of Solids and Structures
International Journal of Solids and Structures, 2023, 268, pp.112170. ⟨10.1016/j.ijsolstr.2023.112170⟩
ISSN: 0020-7683
DOI: 10.1016/j.ijsolstr.2023.112170⟩
Popis: 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
Databáze: OpenAIRE
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