Nonlinear free vibration analysis of rotating composite Timoshenko beams

Arvin, Hadi; Bakhtiari-Nejad, Firooz

doi:10.1016/j.compstruct.2012.09.009

Cited by 54 publications

(33 citation statements)

References 12 publications

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“…Tolga and Metin [7] examined the vibration of rotating composite beams using different beam theories including Euler-Bernoulli, Timoshenko and Reddy theories. Arvin and Bakhtiari [8] studied the linear and nonlinear free vibration of rotating composite Timoshenko beams through Galerkin discretization approach. The similar problems have been discussed by some researchers in the previous studies [9][10][11][12].…”

Section: Introductionmentioning

confidence: 99%

Flapwise free vibration characteristics of a rotating composite thin-walled beam under aerodynamic force and hygrothermal environment

Qin

Yang

et al. 2016

Composite Structures

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Section: Introductionmentioning

confidence: 99%

Flapwise free vibration characteristics of a rotating composite thin-walled beam under aerodynamic force and hygrothermal environment

Qin

Yang

et al. 2016

Composite Structures

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“…Huang [10], and Shen [11] studied the linear dynamic response, too. For the nonlinear free vibration can be seen in [12] of Arvin and Bakhtiari-Nejad. In addition to the Timoshenko beam theory (TBT), the higher-order beam theory (HBT) is also considered, in which The dynamic problem is carried out by Chakrabarti in [13] with FEM. Chakrabarti and colleagues [14,15] analyzed a static problem for two-layer composite beams.…”

Section: Introductionmentioning

confidence: 99%

Finite Element Modelling of a Composite Shell with Shear Connectors

Nguyen

Canh²,

Thanh

et al. 2019

Symmetry

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A three-layer composite shell with shear connectors is made of three shell layers with one another connected by stubs at the contact surfaces. These layers can have similar or different geometrical and physical properties with the assumption that they always contact and have relative movement in the working process. Due to these characteristics, they are used widely in many engineering applications, such as ship manufacturing and production, aerospace technologies, transportation, and so on. However, there are not many studies on these types of structures. This paper is based on the first-order shear deformation Mindlin plate theory and finite element method (FEM) to establish the oscillator equations of the shell structure under dynamic load. The authors construct the calculation program in the MATLAB environment and verify the accuracy of the established program. Based on this approach, we study the effects of some of the geometrical and physical parameters on the dynamic responses of the shell.

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“…In the last 10 years, various nonlinear theories of composite structure have been successfully used in vibration analysis and aeroelastic control for beams or blades, and various optimization approaches using the finite element model (FEM) or various optimization criteria have been used in structural enhancement or active control to achieve the purpose of improving the aeroelastic behavior of blades. The vibration analysis of a rotary composite structure using assumptions of Timoshenko beam theory and exhibiting nonlinear von-Karman strain-displacement relationships has been investigated, with the three-coupled partial differential equation of vibration motion obtained [6]. Aeroelastic stability analysis of a full-scale composite blade has been investigated, with the aerodynamic loading determined using modified Blade Element momentum (BEM) theory and CFD method.…”

Section: Introductionmentioning

confidence: 99%

Sliding Mode Control of Active Trailing-Edge Flap Based on Adaptive Reaching Law and Minimum Parameter Learning of Neural Networks

et al. 2020

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Theoretical modeling and the sliding mode control (SMC) of an active trailing-edge flap of a wind turbine blade based on the adaptive reaching law are investigated. The blade is a single-celled thin-walled composite structure using circumferentially asymmetric stiffness (CAS) design, exhibiting displacements of flap-wise/twist coupling. A reduced structural model originated from the variation method is used to model the structure of the blade, the structural damping of which is computed. The trailing-edge flap is a rigid structure that is embedded in and hinged to the blade host structure, and it is driven by two pairs of pneumatic cylinders moving in reverse. Flutter suppression for the large-amplitude vibration of the blade tip is investigated based on an active trailing-edge flap structure and SMC algorithm using the adaptive reaching law. The controlled responses of flap-wise/twist displacements and control inputs (the angles of the trailing-edge flap) are illustrated, with obvious simulation effects demonstrated. An experimental platform for driving the pneumatic cylinders verifies the effectiveness of the control algorithm using the adaptive reaching law and the effectiveness of the selected pneumatic transmission scheme controlled by another adaptive SMC based on the minimum parameter learning of neural networks.

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Nonlinear free vibration analysis of rotating composite Timoshenko beams

Cited by 54 publications

References 12 publications

Flapwise free vibration characteristics of a rotating composite thin-walled beam under aerodynamic force and hygrothermal environment

Flapwise free vibration characteristics of a rotating composite thin-walled beam under aerodynamic force and hygrothermal environment

Finite Element Modelling of a Composite Shell with Shear Connectors

Sliding Mode Control of Active Trailing-Edge Flap Based on Adaptive Reaching Law and Minimum Parameter Learning of Neural Networks

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