Active Stiffening and Active Damping Effects on Closed Loop Vibration Control of Composite Beams and Plates

Raja, S.; Sinha, P. P.; Prathap, Gangan

doi:10.1177/0731684403027610

Cited by 6 publications

(3 citation statements)

References 16 publications

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“…The numerical analyses indicate that the natural frequencies and the corresponding modes of the laminated structures with two sets of PZT elements can be significantly altered by induced in-plane stresses. The impact of the stiffening and damping effects due to piezoelectric actuators and sensors on the composite structures vibrations control has been studied by Raja et al [15]. Authors observe that the stiffening effect caused by the active element is more pronounced for the vibrations of relatively high amplitudes.…”

Section: Introductionmentioning

confidence: 95%

Influence of the piezoelectric parameters on the dynamics of an active rotor

Gawryluk¹,

Mitura²,

Teter³

2018

AIP Conference Proceedings

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ARTICLES YOU MAY BE INTERESTED INFoldover effect and energy output from a nonlinear pseudo-maglev harvester AIP Conference Proceedings 1922, 100009 (2018 Abstract. The main aim of this paper is an experimental and numerical analysis of the dynamic behavior of an active rotor with three composite blades. The study focuses on developing an effective FE modeling technique of a macro fiber composite element (denoted as MFC or active element) for the dynamic tests of active structures. The active rotor under consideration consists of a hub with a drive shaft, three grips and three glass-epoxy laminate blades with embedded active elements. A simplified FE model of the macro fiber composite element exhibiting the d 33 piezoelectric effect is developed using the Abaqus software package. The discussed transducer is modeled as quasi-homogeneous piezoelectric material, and voltage is applied to the opposite faces of the element. In this case, the effective (equivalent) piezoelectric constant d 33 * is specified. Both static and dynamic tests are performed to verify the proposed model. First, static deflections of the active blade caused by the voltage signal are determined by numerical and experimental analyses. Next, a numerical modal analysis of the active rotor is performed. The eigenmodes and corresponding eigenfrequencies are determined by the Lanczos method. The influence of the model parameters (i.e., the effective piezoelectric constant d 33 * , voltage signal, angular velocity) on the dynamics of the active rotor is examined. Finally, selected numerical results are validated in experimental tests. The experimental findings demonstrate that the structural stiffening effect caused by the active element strongly depends on the value of the effective piezoelectric constant.

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Section: Introductionmentioning

confidence: 95%

Influence of the piezoelectric parameters on the dynamics of an active rotor

Gawryluk¹,

Mitura²,

Teter³

2018

AIP Conference Proceedings

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“…The feedback voltage is obtained by amplifying the sensor signal with a suitable gain. The experimental implementation of displacement and velocity feedback using PZT sensors has been broadly discussed [23].…”

Section: Active Vibration Control Studies On the Active Aeroelastimentioning

confidence: 99%

Active Control of Wing Flutter Using Piezoactuated Surface

Raja

Upadhya

2007

Journal of Aircraft

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A flutter suppression concept is demonstrated by performing wind-tunnel tests in a low subsonic flow regime. The wing model, with a trailing edge control surface, is constructed to have a bending-torsion flutter. The control surface is actuated by a flexure-hinged lead zirconate titanate stack mechanism acting as an aerodynamic effector. The flutter experiments are conducted using a digital controller, implemented in dSPACE DS1104, keeping the wing model at 4 deg angle of attack. The wing response is measured by lead zirconate titanate sensors, which are used to generate the feedback control to vibrate the control surface in antiphase motion with respect to the main surface to introduce active aerodynamic control. It is noticed that both bending and torsion modes are stabilized in closed-loop configurations. The damping trend of the flutter mode shows an expanded flutter envelope that is estimated to be around 20%. The actuators are operated within 1000 V=mm, though their allowable field strength is 1500 V=mm.

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“…Rao and Ganesan presented the harmonic response of tapered composite beams by using the finite element method [3]. Raja et al [4] presented the free and forced harmonic vibration control of composite beams by active stiffening method using piezo patches. They reported that the active stiffening effect through displacement control is more effective for smaller modes.…”

Section: Introductionmentioning

confidence: 99%

Numerical Investigation of the Dynamic Response of Symmetric Laminated Composite Beams to Harmonic Excitations

Kıral

2009

Advanced Composites Letters

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The aim of this study is to investigate the dynamic response of a laminated composite beam subjected to a harmonic excitation by a numerical time integration method known as Newmark method. The finite element method based on the classical laminated plate theory is used in order to obtain structural stiffness. The structural damping is modelled as proportional damping which is referred to as Rayleigh damping and two different damping ratios are used. The effect of damping on the frequency response of the beam is investigated for a broad range of excitation frequency. The effect of excitation point on the harmonic response is also considered. Four different lay-up configurations namely [0] 2s , [0/90] s , [45/-45] s and [90] 2s are considered in order to show the effect of the stacking sequence on the frequency response of the beam. The numerical results presented in this study show that, the magnitude of the harmonic response of the beam reduces considerably as the damping ratio increases and [90] 2s lay-up produces largest dynamic response due to the reducing flexural rigidity. Numerical results also show that the location and frequency of the harmonic excitation has important role on the dynamic response of the beam.

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Active Stiffening and Active Damping Effects on Closed Loop Vibration Control of Composite Beams and Plates

Cited by 6 publications

References 16 publications

Influence of the piezoelectric parameters on the dynamics of an active rotor

Influence of the piezoelectric parameters on the dynamics of an active rotor

Active Control of Wing Flutter Using Piezoactuated Surface

Numerical Investigation of the Dynamic Response of Symmetric Laminated Composite Beams to Harmonic Excitations

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