An experimental and numerical study of piezoceramic actuator hysteresis in helicopter active vibration control

Mallick, Rajnish; Ganguli, Ranjan; Bhat, M. Seetharama

doi:10.1177/0954410013478254

Cited by 17 publications

(15 citation statements)

References 37 publications

(31 reference statements)

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“…Although the hysteresis behavior of this actuator strengthened as the increase in actuation frequency, the amplitude of the output stroke nearly remained constant, revealing a wide operational bandwidth of this actuator. In addition, the asymmetry of the hysteresis curves, which could be attributed to properties of the selected piezoelectric stack, made it difficult to be modeled using the theory of conic sections which had been utilized in [13]. The hysteresis curves of this actuator at different frequencies are presented in Figure 3.…”

Section: Piezoelectric Actuator and Its Hysteresis Behaviormentioning

confidence: 99%

“…Simulation results demonstrated that a vibration reduction of 90% could be achieved if actuator hysteresis was compensated, while it decreased to 69% without compensation. Rajnish et al [13] built a rate-dependent hysteresis model for an APA500L actuator using theory of conic sections based on experimental data. Eric et al [14,15] built a hysteresis model using the classical Preisach model based on experimental data, which was incorporated into the aero-elastic analysis code.…”

Section: Introductionmentioning

confidence: 99%

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Hysteresis Compensation for a Piezoelectric Actuator of Active Helicopter Rotor Using Compound Control

2021

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Active rotor with trailing-edge flaps is a promising method to alleviate vibrations and noise level of helicopters. Hysteresis of the piezoelectric actuators used to drive the flaps can degrade the performance of an active rotor. In this study, bench-top tests are conducted to measure the nonlinear hysteresis of a double-acting piezoelectric actuator. Based on the experimental data, a rate-dependent hysteresis model is established by combining a Bouc–Wen model and a transfer function of a second order system. Good agreement is exhibited between the model outputs and the measured results for different frequencies. A compound control regime composed of a feedforward compensator and PID (Proportional–Integral–Derivative) feedback control is developed to suppress the hysteresis of this actuator. Bench-top test results demonstrate that this compound control regime is capable to suppress hysteresis at different frequencies from 10 Hz to 60 Hz, and errors between the desired actuator outputs and the measured outputs are reduced dramatically at different frequencies, revealing that this compound control regime has the potential to be implemented in an active helicopter rotor to suppress actuator hysteresis.

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Section: Piezoelectric Actuator and Its Hysteresis Behaviormentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Hysteresis Compensation for a Piezoelectric Actuator of Active Helicopter Rotor Using Compound Control

2021

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“…Hysteresis is a lagging phenomenon where a physical effect on the smart material lags behind its cause. When a smart material acts as an actuator or a sensor of space structure, the response of the smart structure lags behind the input excitation of the system [4,5]. e nonlinearity not only affects the control precision of the smart structure with a control law but also threatens the stability of the control system [6].…”

Section: Introductionmentioning

confidence: 99%

Influence of Hysteresis on the Vibration Control of a Smart Beam with a Piezoelectric Actuator by the Bouc–Wen Model

Zhang

2020

Shock and Vibration

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The hysteresis property in a smart structure has attracted much attention from researchers for several decades. Hysteresis not only affects the response precision of the smart structure but also threatens the stability of the system. This paper focuses on how the hysteresis property influences the control effect of vibration suppression for a smart beam. Furthermore, the Bouc–Wen model is adopted to describe the hysteresis property of a smart beam and the hysteresis parameters of the hysteresis model are identified with a genetic algorithm. Based on the identification results, the hysteresis model is validated to represent the hysteresis property of the smart beam. Based on the hysteresis model, model reference adaptive control is designed to explore the influence of hysteresis on the vibration control of the smart beam. With some simulations and experiments, it is found that the vibration control effect is influenced when the hysteresis item changes. The vibration control effect will be improved when the hysteresis coefficient in the Bouc–Wen model, as the expected objective model of the adaptive reference model, is within a proper numerical range where the control system is stable. Furthermore, when the time delay is considered in the closed-loop control system, the principle of the hysteresis influence is different. The results indicate that the hysteresis property affects not only the control effect but also the stability of the control system for a smart cantilever beam.

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“…(2013) quantified the capabilities of the trailing-edge flaps for helicopter vibration reduction and performance improvement using the comprehensive analysis, University of Maryland Advanced Rotor Code. Mallick et al . (2014) conducted numerical and experimental study for the piezoceramic actuator hysteresis.…”

Section: Introductionmentioning

confidence: 99%

Design improvements and flap deflection evaluations with considering centrifugal load on active trailing edge flap

Visconti

Eun

Sim

et al. 2018

AEAT

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Purpose The purpose of this paper is to present the design, analysis and experiments of the active trailing-edge flap (Seoul National University Flap, SNUF) for vibration reduction in the helicopter rotor prior to the small-scale blades planned to test in a whirl tower. Design/methodology/approach The predictions of the hinge moment in both steady and unsteady flows were obtained through computational fluid dynamics calculations. When compared with the results originated from analytical formulations, the proposed method showed improved prediction capabilities. To validate the deflection of the flap under the centrifugal load by rotating, static analysis was conducted using both contact and rotating condition of MSC NASTRAN. The corresponding experiment also was performed using the vertical frame for simulating the effect of the centrifugal force. Findings The hinge moment of the flap is predicted through unsteady analysis in the actuation frequency of 3/rev. The material of the guide in the flap mechanism was selected through static analysis under both contact and rotating condition. Finally, reduction of the deflection occurred because of the load in the axial direction of the hinge like the centrifugal load. Practical implications The important aspects, such as design, analysis, and experiments for the active trailing-edge flap were shown. Originality/value This paper showed the relationship of the displacement, block force and voltage of the piezo-actuator, combined with the hinge moment predicted. The methodology and the experiment were presented for simulating the centrifugal force acting on the flap.

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An experimental and numerical study of piezoceramic actuator hysteresis in helicopter active vibration control

Cited by 17 publications

References 37 publications

Hysteresis Compensation for a Piezoelectric Actuator of Active Helicopter Rotor Using Compound Control

Hysteresis Compensation for a Piezoelectric Actuator of Active Helicopter Rotor Using Compound Control

Influence of Hysteresis on the Vibration Control of a Smart Beam with a Piezoelectric Actuator by the Bouc–Wen Model

Design improvements and flap deflection evaluations with considering centrifugal load on active trailing edge flap

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