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Effect of Eccentricity on Nonlinear Galloping of Cables

Paper Type: Free Essay Subject: Engineering
Wordcount: 5750 words Published: 31st Aug 2017

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The Effect of Eccentricity on the Nonlinear Galloping of Cables under Combined Wind Flow and Support motion in 1:1 Internal, External and Parametric Resonance Condition

Amir Jalali Saman Sadripour

Department of Mechanical Engineering, Shahrood University of Technology, Shahrood, Iran.

Galloping of cables is a kind of self-excited vibration and characterized with high amplitude and low frequency. In this paper for investigating the nonlinear galloping of an inclined cable, considering flexural and torsional stiffness, a cable-beam model is used. The iced cable is formulated under the effects of combined wind flow and support motion. Assuming low sag to span ratio and using physical parameter values of the cable, the governing equation of motion is obtained as a classical equations of the perfectly flexible cable, plus a further equation governing the twist motion. These two degrees of freedom system is discretized via the Galerkin method, by taking one in-plane and one out-of-plane modes as trial function. Two resulting non-homogeneous ordinary differential equations are coupled and contain quadratic and cubic nonlinearities in both velocity and displacement terms. By using multiple scale method for 1:1 internal resonance and 1:1 external resonance, a first order amplitude-phase modulation equation, governing the slow dynamic of the cable, is obtained. In this paper the wind speed and the eccentricity of the iced section are set as control parameters. Without consideration the eccentricity, the value of amplitude is increased as the wind speed is increase. But considering the eccentricity reduced to firstly increasing and then decreasing the amplitude.

Keywords:Galloping, Stiff Cable, Wind Flow, Eccentricity, Perturbation method

  1. Introduction

Cables are light and flexible structures which are used commonly in many engineering structures. Because of their low inherent damping, Cables are exposed to wind-induced vibration. Galloping is a classic phenomenon of aerodynamic instability of slender structures having non-circular cross sections [analytical]. A circular cylinder, with perfect symmetry will not exhibit galloping, though galloping is a common occurrence of on ice-laden cables, where the ice introduces the required asymmetry [1]. Galloping is characterized by low frequency and high amplitude vibration and has many roles in the field of cable vibration. The effects of galloping on a transmission line is dependent upon the severity and duration of the galloping event but typical problems are phase to phase flashover causing outages and arcing damage to conductors, loosening of tower bolts and damage to suspension and tension clamps, spacers and vibration dampers and, in some critical cases, structural damage to towers [1]. In order to prevent these damages, it is important to study on this kind of vibration.

The initial galloping model was proposed by Irvine [1], this model is based on the low sag to span ratio. The first studies of galloping considered it to be single degree of freedom (mono-modal galloping); Den Hartog [1] and Parkinson [1] introduce a model by consideration the vertical direction for galloping motion. Jones [1] and Luongo [1] proposed a two degree of freedom model by consideration vertical and horizontal motion and the interaction between them. In a major advance in (2010) Blevins [1] and Yu et al. [1] analyzed the effect of rotation on galloping and have found that the rotation plays an important role on the initiation of galloping under certain conditions. After that Yu [1, 2] proposed a three degree of freedom galloping model (vertical, horizontal and rotational) by consideration eccentricity of ice. The 3-DOF models have been used widely in galloping analysis using analytical and finite element methods. All these models consider the cable as a flexible structure and cannot consider the bending effects. Luongo [10-12] proposed a new model for considering both bending and rotation. This new model is based on the curved-beam theory and importance of consideration bending effects has been proved in linear [1] and nonlinear regime [1] under internal resonance conditions, devoting attention to the comparison between analytical and numerical approaches [1].

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In the present paper, to investigate the effect of eccentricity on the iced cables which exposed to wind flow and support motion simultaneously, a nonlinear curved beam model [1] is introduced. The proposed model in this paper, is a nonlinear model of an inclined cable which able to twist and displacement in three normal, bi-normal and tangential directions. By using strain-displacements relation and based on Hamilton principle equations of motion can be derived. The aerodynamic forces are modeled referring to the quasi-steady theory, and they depend on the mean wind speed and on the angle of attack. Moreover, according to the property of the sample cable and Galerkin method, by considering one in-plane and one out-of-plane modes, a simplified two-degree of-freedom (normal and bi-normal) model with consideration of torsion, bending and eccentricity has been obtained. The two resulting equations are second order, non-homogeneous, time-periodic, ordinary differential equations and coupled with quadratic and cubic nonlinearities, both in the displacements and velocities. By using multiple scale method for 1:1 internal resonance between the in-plane and out-of-plane modes, and 1:1 external resonance between forcing and natural frequencies, a first order amplitude-phase modulation equation, governing the slow dynamic of the cable, is obtained. In this paper the wind speed, the eccentricity of the iced section and the amplitude of the support motion are set as control parameters.

The paper is organized as follows:

In the section 2 the equations of motion are formulated based on Hamiltonian theory. The reduced equations of motion are derived with simplifying assumption in section 3. By defining the non-dimensional parameters, Dimensionless equations are obtained in section 4. In the section 5 aerodynamic forces are formulated based on quasi-steady theory. Discretizing via Galerkin procedure is performed in the next section and the perturbation analysis is carried out in section 7, where the amplitude modulation equations are derived. Finally for a sample system, some conclusions are drawn in section 8.

  1. Mechanical model

The cable is modeled as a body made of a flexible centerline and rigid cross-sections restrained to remain orthogonal to the axis (shear-undeformable beam). It is assumed to be uniformly iced and loaded by a wind flow of mean velocity , blowing horizontally. For better description of cable-beam model, the choice of coordinates is made as following: directions 1,2 and 3 denote tangential, normal and bi-normal directions of transmission line, respectively. Four different configurations are considered. (a) the configuration, taken by the body at time and the cable is under the action of gravity including ice, in this configuration the cable is in a vertical plane belong to (x,y) plane so the cross-section is in the (y,z) plane. (b) the configuration, in this configuration the eccentricity of cross-section due to ice layer is considered. Because of eccentricity of iced transmission line, the configuration rotates the initial angle from shape . (c) the reference configuration is considered by the body at time , it is assumed in which static aerodynamic forces act on transmission line. Due to static aerodynamic forces the cross section rotates the angle from the shape , this configuration is described by planner curve and by the cross-section inertial principal triad assumed to be coincident with the Frenet triad [1]. (d) the actual configuration is considered at time , it is assumed all forces including static and dynamic forces and support motion act on the body, The actual configuration of the body is described by the non-planar curve and the inertial principal triad . Because of the dynamic part of aerodynamic force, the dynamic rotation and transport is described by and the displacement vector field , respectively.



According to [2, 3], assuming low sag to span ratio, the Lagrange strain-displacement relationship can be calculated as below:





Where is stretching, is torsion, and are bending strains, respectively and are the components of displacement vector in basis . “” Is the initial curvature of the cable and “” is the twist of the cross section. All the displacements and twist depends on the curvilinear abscissa “” and time ““. Based on [1] the equations of motion were derived via extended Hamilton principle by ignoring the shear resistance of the curved beam.


Where ; ; , are the first moment of area about and axes. Is tensional, is the torsional, and are the bending forces all at time ““. The sign ”.” denotes derivation with respect time ““; and represent eccentricity of cross section about the and axes, respectively; is the density of transmission line; is the area of cross section; , , , and are the axial, bending and torsional stiffness, respectively; , and are aerodynamic forces; , , and are structural damping coefficients; denotes the cable length. Represents the horizontal distance between adjacent towers; is sag at the mid-span.

Based on [1] by reducing strain-displacement equations (1) – (1) to equations (1) – (1) and substituting them into equation (1), the equations of motion (1) – (1) with boundary condition (1) – (1) can be obtained in the four directions.




Tangential direction:


Normal direction:


Bi-normal direction:


Torsional direction:






Where sign ” ´ ” denotes differentiation with respect to ““.

  1. Reduced equations of motion

Since the transversal-to-longitudinal (or torsional) squared frequency ratio is small, stretching and torsion are quasi-steady, so that inertial and damping forces can be neglected in the relevant equations. By substituting Longitudinal displacements are consequently statically condensed as (1) where the boundary conditions (1) have been used. Furthermore , in equation (1) are assumed as and respectively. Thus equations (1) and (1) can be simplified as:



According to the actual transmission line properties, and are very small compared with area of cable cross section , therefore and in equations (1) and (1) can be ignored. Since the equation in twist direction cannot be condensed such a simple way, it is convenient to use twist equation as an ancillary equation in the following. By substituting (1) in equations (1) to (1), the equations of motion can be obtained as equations (1) to (1) by boundary condition (1) to (1).







Since the equations of motion (1) to (1) have non-homogenous boundary conditions, by considering transformation (1) the system can be transform into an equivalent system with homogenous boundary condition.


In which is quasi-static and is dynamic component of the solution and they can be obtained by solving the linearized, non-homogenous system that is describe planner, linear, static of the cable, when a vertical unitary time-independent motion of the support is applied [1].



The particular solution of equation (1) can be obtained as follow:



  1. Dimensionless form of equations

By defining non-dimensional parameter (1), dimensionless forms of equations of motion are obtained as follow:





In which all ‘*’ Superscripts have been eliminating in order to simplicity and non-dimensional parameters are introduced as follow:


Where the index ‘n’ used instead of value and .

  1. Aerodynamic forces

In order to gain a simple aerodynamic model, simplifying assumption should be considered. a) The quasi-steady theory is adopted [1], b) the curvature of cable is neglected, c) the twist angle is accounted in loads but the effect of flexural rotation is neglected, d) the ice is uniformly cover the cable surface and e) the aerodynamic couples are neglected. Based on these assumptions aerodynamic forces and can be obtained. As shown in figure (1) wind blow with speed to cable plane, expression (1) denotes projection of this speed on the plane of cross section. The angle of attack introduced by the angle between direction of the component of wind speed on the cross section and a reference direction (hear the reference direction is adopted axis ), equation (1) and (1) express these concepts.



Based on quasi-steady theory the aerodynamic force can be calculated by


Where is angle of attack, is the relative velocity between the wind speed and structure speed, is air density, is characteristic radius of section, the modulus of relation speed, and are lift and drag coefficient respectively and they’re dependent on the angle of attack and written as



In which is defined as relation (1) and are the aerodynamic coefficients in reference configuration that are obtained by experimental results.


By substituting these expression into (1) and projecting this equation on direction and the components of aerodynamic force and can be calculated as follow:


For and where is a vector that collecting all the invariable components, , and are the coefficients that depend on the , and their derivati


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