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A platform for research: civil engineering, architecture and urbanism
Geometrically nonlinear dynamic analysis of variable stiffness composite laminated and sandwich shell panels
https://orcid.org/0000-0001-9011-5343
https://orcid.org/0000-0002-5554-3788
Abstract The nonlinear free and forced vibration analyses of variable stiffness composite laminated (VSCL) and sandwich shell panels having curvilinear fibres, not yet reported in literature, are conducted based on a higher-order theory. The present structural model considers a third-order shear deformation theory incorporating Murakami zig-zag effects. The analyses are performed using C0 nine-noded isoparametric element with thirteen degrees of freedom and geometrical nonlinearity is included through von Kármán nonlinear strain–displacement relations. The free and forced vibrational responses of the VSCL are established using the eigenvalue solutions and Newmark’s time integration technique, respectively. The results obtained using the present finite element formulation are compared with the available three-dimensional exact and two-dimensional analytical and numerical solutions for establishing the validity of the model. The fundamental frequencies and nonlinear transient deflections of VSCL and sandwich spherical and cylindrical shell panels are evaluated considering the effects of curvilinear fibre path, curvature ratio, number of layers and lamination configuration.
Highlights Analysed nonlinear vibration behaviour of composite laminated and sandwich shell panels with curvilinear fibres. A finite element formulation based on Murakami zig-zag theory with thirteen degrees of freedom per node is considered. Nonlinear dynamic behaviour of VSCL and sandwich shell panels investigated for the first time. Dynamic response is affected by the curvilinear fibre orientation for VSCL structures.
Geometrically nonlinear dynamic analysis of variable stiffness composite laminated and sandwich shell panels
https://orcid.org/0000-0001-9011-5343
https://orcid.org/0000-0002-5554-3788
Abstract The nonlinear free and forced vibration analyses of variable stiffness composite laminated (VSCL) and sandwich shell panels having curvilinear fibres, not yet reported in literature, are conducted based on a higher-order theory. The present structural model considers a third-order shear deformation theory incorporating Murakami zig-zag effects. The analyses are performed using C0 nine-noded isoparametric element with thirteen degrees of freedom and geometrical nonlinearity is included through von Kármán nonlinear strain–displacement relations. The free and forced vibrational responses of the VSCL are established using the eigenvalue solutions and Newmark’s time integration technique, respectively. The results obtained using the present finite element formulation are compared with the available three-dimensional exact and two-dimensional analytical and numerical solutions for establishing the validity of the model. The fundamental frequencies and nonlinear transient deflections of VSCL and sandwich spherical and cylindrical shell panels are evaluated considering the effects of curvilinear fibre path, curvature ratio, number of layers and lamination configuration.
Highlights Analysed nonlinear vibration behaviour of composite laminated and sandwich shell panels with curvilinear fibres. A finite element formulation based on Murakami zig-zag theory with thirteen degrees of freedom per node is considered. Nonlinear dynamic behaviour of VSCL and sandwich shell panels investigated for the first time. Dynamic response is affected by the curvilinear fibre orientation for VSCL structures.
Geometrically nonlinear dynamic analysis of variable stiffness composite laminated and sandwich shell panels
https://orcid.org/0000-0001-9011-5343
https://orcid.org/0000-0002-5554-3788
Abstract The nonlinear free and forced vibration analyses of variable stiffness composite laminated (VSCL) and sandwich shell panels having curvilinear fibres, not yet reported in literature, are conducted based on a higher-order theory. The present structural model considers a third-order shear deformation theory incorporating Murakami zig-zag effects. The analyses are performed using C0 nine-noded isoparametric element with thirteen degrees of freedom and geometrical nonlinearity is included through von Kármán nonlinear strain–displacement relations. The free and forced vibrational responses of the VSCL are established using the eigenvalue solutions and Newmark’s time integration technique, respectively. The results obtained using the present finite element formulation are compared with the available three-dimensional exact and two-dimensional analytical and numerical solutions for establishing the validity of the model. The fundamental frequencies and nonlinear transient deflections of VSCL and sandwich spherical and cylindrical shell panels are evaluated considering the effects of curvilinear fibre path, curvature ratio, number of layers and lamination configuration.
Highlights Analysed nonlinear vibration behaviour of composite laminated and sandwich shell panels with curvilinear fibres. A finite element formulation based on Murakami zig-zag theory with thirteen degrees of freedom per node is considered. Nonlinear dynamic behaviour of VSCL and sandwich shell panels investigated for the first time. Dynamic response is affected by the curvilinear fibre orientation for VSCL structures.
Geometrically nonlinear dynamic analysis of variable stiffness composite laminated and sandwich shell panels
Gupta, Ankita (author) / Pradyumna, S. (author)
Thin-Walled Structures ; 173
2022-02-03
Article (Journal)
Electronic Resource
English
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