Finite element analysis of composite revolution structures wound by wide plies |
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| Affiliation: | 1. CONICET, INTEC, Güemes 3450, 3000 Santa Fe, Argentina;2. IRSIA, Aerospace Laboratory of Liège University, Rue E. Solvay, 21, B-4000, Liège, Belgium;3. Aérospatiale, Etablissement d''Aquitaine, BP11, F-33165, Saint Médard en Jalles, France;1. INEGI – Instituto de Ciência e Inovação em Engenharia Mecânica e Engenharia Industrial, Rua Dr. Roberto Frias 400, 4200-465 Porto, Portugal;2. Faculdade de Engenharia da Universidade do Porto, Departamento de Engenharia Mecânica, Rua Dr. Roberto Frias, 4200-465 Porto, Portugal;3. Centre for the Research and Technology of Agro-Environmental and Biological Sciences, CITAB, University of Trás-os-Montes and Alto Douro, UTAD, Quinta de Prados, 5000-801 Vila Real, Portugal;1. Elasticity and Strength of Materials Group, School of Engineering, University of Seville, Camino de los Descubrimientos s/n, 41092, Seville, Spain;2. TEAMS, Testing and Engineering of Aeronautical Materials and Structures, Wilbur & Orville Wright, 1 Aerospace Technology Park of Andalusia, Aeropolis 41309 La Rinconada, Seville, Spain;1. Fatigue and Fracture Research Laboratory, Center of Excellence in Experimental Solid Mechanics and Dynamics, Department of Mechanical Engineering, Iran University of Science and Technology, Narmak 16846, Tehran, Iran;2. NTNU Department of Engineering Design and Materials, Richard Birkelands vei 2b, 7491 Trondheim, Norway |
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| Abstract: | An isoparametric axisymmetrical finite element is developed for the analysis of multilayer composite structures wound by wide plies. This element takes into account the variation of angle along the width of a layer for a given parallel of a revolution structure. Evaluation of strain and stress tensors is performed in mean and extreme fibre directions of a ply. Moreover, this model can represent geometrical nonlinear behaviour and material nonlinearities. The extended possibilities of this model are illustrated for two aerospace structures: a spherical wound satellite tank and the composite head of a rocket motor. |
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