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

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...

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Autores principales:	Jinlong Zhou, Linghua Dong, Weidong Yang
Formato:	article
Lenguaje:	EN
Publicado:	MDPI AG 2021
Materias:	helicopter trailing-edge flap piezoelectric actuator hysteresis compound control Mechanical engineering and machinery TJ1-1570
Acceso en línea:	https://doaj.org/article/bbe7522e4f234b24b8c6d59729ef42c3
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id	oai:doaj.org-article:bbe7522e4f234b24b8c6d59729ef42c3
record_format	dspace
spelling	oai:doaj.org-article:bbe7522e4f234b24b8c6d59729ef42c32021-11-25T18:22:55ZHysteresis Compensation for a Piezoelectric Actuator of Active Helicopter Rotor Using Compound Control10.3390/mi121112982072-666Xhttps://doaj.org/article/bbe7522e4f234b24b8c6d59729ef42c32021-10-01T00:00:00Zhttps://www.mdpi.com/2072-666X/12/11/1298https://doaj.org/toc/2072-666XActive 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.Jinlong ZhouLinghua DongWeidong YangMDPI AGarticlehelicoptertrailing-edge flappiezoelectric actuatorhysteresiscompound controlMechanical engineering and machineryTJ1-1570ENMicromachines, Vol 12, Iss 1298, p 1298 (2021)
institution	DOAJ
collection	DOAJ
language	EN
topic	helicopter trailing-edge flap piezoelectric actuator hysteresis compound control Mechanical engineering and machinery TJ1-1570
spellingShingle	helicopter trailing-edge flap piezoelectric actuator hysteresis compound control Mechanical engineering and machinery TJ1-1570 Jinlong Zhou Linghua Dong Weidong Yang Hysteresis Compensation for a Piezoelectric Actuator of Active Helicopter Rotor Using Compound Control
description	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.
format	article
author	Jinlong Zhou Linghua Dong Weidong Yang
author_facet	Jinlong Zhou Linghua Dong Weidong Yang
author_sort	Jinlong Zhou
title	Hysteresis Compensation for a Piezoelectric Actuator of Active Helicopter Rotor Using Compound Control
title_short	Hysteresis Compensation for a Piezoelectric Actuator of Active Helicopter Rotor Using Compound Control
title_full	Hysteresis Compensation for a Piezoelectric Actuator of Active Helicopter Rotor Using Compound Control
title_fullStr	Hysteresis Compensation for a Piezoelectric Actuator of Active Helicopter Rotor Using Compound Control
title_full_unstemmed	Hysteresis Compensation for a Piezoelectric Actuator of Active Helicopter Rotor Using Compound Control
title_sort	hysteresis compensation for a piezoelectric actuator of active helicopter rotor using compound control
publisher	MDPI AG
publishDate	2021
url	https://doaj.org/article/bbe7522e4f234b24b8c6d59729ef42c3
work_keys_str_mv	AT jinlongzhou hysteresiscompensationforapiezoelectricactuatorofactivehelicopterrotorusingcompoundcontrol AT linghuadong hysteresiscompensationforapiezoelectricactuatorofactivehelicopterrotorusingcompoundcontrol AT weidongyang hysteresiscompensationforapiezoelectricactuatorofactivehelicopterrotorusingcompoundcontrol
_version_	1718411282107858944

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

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