Transient Dynamic Response of Clamped-Free Hybrid Composite Circular Cylindrical Shells |
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| Authors: | Keramat Malekzadeh S. Mohammad Reza Khalili Ali Davar Puneet Mahajan |
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| Affiliation: | (1) Department of Mechanical Engineering, Malek Ashtar University of Technology, Karaj Makhsous Rd., Tehran, Iran;(2) Centre of Excellence for Research in Advanced Materials & Structures, Faculty of Mechanical Engineering, K.N. Toosi University of Technology, Tehran, Iran;(3) Faculty of Engineering, Kingston University, London, UK;(4) Department of Applied Mechanics, Indian Institute of Technology, New Delhi, 110016, India; |
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| Abstract: | Dynamic response of multilayer circular cylindrical shells composed of hybrid composite materials subjected to lateral impulse load is studied in this paper. The boundary conditions (B.C.s) are considered to be clamped-free. Both isotropic (metal) and orthotropic (composite) layers are used simultaneously in the hybrid lamination. There is no limitation for fibre orientation. First order shear deformation theory (FSDT) and Love’s first approximation theory are utilized in the shell’s equilibrium equations. Equilibrium equations for free and forced vibration problems of the shell are solved using Galerkin method. Finally, time response of displacement components of Fibre-Metal Laminate (FML) cylindrical shells is derived using mode superposition method. The effect of lay up, material properties, fibre orientation and volume fraction of metal layers on the dynamic response of the shell are investigated. New interesting results are obtained and discussed providing a helpful insight for aircraft structure’s designers. |
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