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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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Detalles Bibliográficos
Autores principales: Zhou, Jinlong, Dong, Linghua, Yang, Weidong
Formato: Online Artículo Texto
Lenguaje:English
Publicado: MDPI 2021
Materias:
Acceso en línea:https://www.ncbi.nlm.nih.gov/pmc/articles/PMC8621093/
https://www.ncbi.nlm.nih.gov/pubmed/34832710
http://dx.doi.org/10.3390/mi12111298
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author Zhou, Jinlong
Dong, Linghua
Yang, Weidong
author_facet Zhou, Jinlong
Dong, Linghua
Yang, Weidong
author_sort Zhou, Jinlong
collection PubMed
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.
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spelling pubmed-86210932021-11-27 Hysteresis Compensation for a Piezoelectric Actuator of Active Helicopter Rotor Using Compound Control Zhou, Jinlong Dong, Linghua Yang, Weidong Micromachines (Basel) Article 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. MDPI 2021-10-22 /pmc/articles/PMC8621093/ /pubmed/34832710 http://dx.doi.org/10.3390/mi12111298 Text en © 2021 by the authors. https://creativecommons.org/licenses/by/4.0/Licensee MDPI, Basel, Switzerland. This article is an open access article distributed under the terms and conditions of the Creative Commons Attribution (CC BY) license (https://creativecommons.org/licenses/by/4.0/).
spellingShingle Article
Zhou, Jinlong
Dong, Linghua
Yang, Weidong
Hysteresis Compensation for a Piezoelectric Actuator of Active Helicopter Rotor Using Compound Control
title 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_short 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
topic Article
url https://www.ncbi.nlm.nih.gov/pmc/articles/PMC8621093/
https://www.ncbi.nlm.nih.gov/pubmed/34832710
http://dx.doi.org/10.3390/mi12111298
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