Measurement of vibrations of a wing

Maskeliūnas, V.; Maskeliūnas, R.; Paškevičius, P.; Ragulskis, L.

doi:10.21595/jme.2016.17772

Cited by 2 publications

(2 citation statements)

References 11 publications

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“…A high-order finite element formulation is developed by Ganesan and Zabehollah [2] for vibration analysis of tapered composite beams. Vibrations measurements of a wing are investigated experimentally by using the method of time averaged projection moiré analyzed by Maskeliūnas et al [3]. Omarov et al [4] made a dynamic model to determinate the reduced mass and stiffness of flexural vibrating cantilever beams.…”

Section: Introductionmentioning

confidence: 99%

Measurement of vibrations of composite wings using high-order finite element beam

Bennamia¹,

Badereddine²,

Zebbiche³

2018

J. meas. eng.

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The purpose of this study is to show the influence of bending-torsion coupling on natural frequencies and mode shapes of aircraft wings by using two finite element beam formulations. The bending-torsion coupling parameters are the geometric parameter (distance between the mass axis and elastic axis of the cross-section of the beam) and the material coupling due to laminated composites. Cubic and high-order Hermite finite element interpolations are presented in this study, in order to show the influence of geometric and material coupling on natural frequencies and mode shapes. Starting by the governing partial differential equations of motion for the coupled bending-torsion beam with the bending and torsion equations, the Galerkin's method is used with high-order finite element interpolation to obtain the high-order Hermitian shape functions. The mass and stiffness matrices are obtained using the kinetic energy and potential energy, respectively. The beam finite element has two nodes, the cubic element has three degrees of freedom at each end (transvers displacement, slope and torsion), where the high order element has five degrees of freedom at each end (transvers displacement, slope, curvature, gradient of curvature and torsion). The mass matrix contains geometric coupling terms and the stiffness matrix contains terms of material bending-torsion coupling. The obtained results using cubic and high-order finite element Euler-Bernoulli beam formulations are compared for a free vibration analysis of Goland metallic wing (geometric coupling) and validated with Dynamic Stiffness Method for composite wings.

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Section: Introductionmentioning

confidence: 99%

Measurement of vibrations of composite wings using high-order finite element beam

Bennamia¹,

Badereddine²,

Zebbiche³

2018

J. meas. eng.

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“…In the previous paper [1] projection moiré measurements of vibrations of a wing were performed, the experimental setup was presented in detail and typical experimental results were described. This paper continues the investigations presented there and is devoted to the investigation of possibilities of application of time averaged reflection moiré techniques to the same problem.…”

Section: Introductionmentioning

confidence: 99%

Reflection moiré for the measurement of wing vibrations

Maskeliūnas¹,

Maskeliūnas²,

Ragulskis³

et al. 2018

J. meas. eng.

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Abstract. Investigation of time averaged reflection moiré measurements of vibrations of a wing is performed in this paper. Interpretation of reflection moiré images on a shallow surface of a wing is more complicated than on a plane surface. For this purpose, a special simplified two-dimensional numerical model is developed and the possibilities of application of this method of measurement of vibrations are investigated.

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Measurement of vibrations of a wing

Cited by 2 publications

References 11 publications

Measurement of vibrations of composite wings using high-order finite element beam

Measurement of vibrations of composite wings using high-order finite element beam

Reflection moiré for the measurement of wing vibrations

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