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Observer-based sliding mode control for piezoelectric wing bending-torsion coupling flutter involving delayed output
An observer-based sliding mode control scheme is proposed for suppressing bending-torsion coupling flutter motions of a wing aeroelastic system with delayed output by using the piezoelectric patch actuators. The wing structure is modeled as a thin-walled beam, and the aerodynamics on the wing are co...
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Published in: | Journal of vibration and control 2021-08, Vol.27 (15-16), p.1824-1841 |
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container_end_page | 1841 |
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container_title | Journal of vibration and control |
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creator | Li, Da Yang, Hui Qi, Na Yuan, Jiaxin |
description | An observer-based sliding mode control scheme is proposed for suppressing bending-torsion coupling flutter motions of a wing aeroelastic system with delayed output by using the piezoelectric patch actuators. The wing structure is modeled as a thin-walled beam, and the aerodynamics on the wing are computed by the strip theory. For the implementation of the control algorithm, the piezoelectric patch is bonded on the top surface of the beam to act as the actuator. Ignoring the effect of piezoelectric actuators on structural dynamics, only considering the bending moments induced by piezoelectric effects, the corresponding dynamic motion equation is established by using the Lagrange method with the assumed mode method. The flutter speed and frequency of the closed-loop system with time delay are obtained by solving a polynomial eigenvalue problem. An observer-based controller that does not dependent on time delay is developed for suppressing the flutter, and the corresponding gain matrices are obtained by solving linear matrix inequalities. The sufficient condition for the asymptotic stability of the closed-loop system is derived in terms of linear matrix inequalities. The simulation results demonstrate that the proposed control strategy based on the piezoelectric actuator is effective in wing bending-torsion coupling flutter system with a delayed output. |
doi_str_mv | 10.1177/1077546320949122 |
format | article |
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The wing structure is modeled as a thin-walled beam, and the aerodynamics on the wing are computed by the strip theory. For the implementation of the control algorithm, the piezoelectric patch is bonded on the top surface of the beam to act as the actuator. Ignoring the effect of piezoelectric actuators on structural dynamics, only considering the bending moments induced by piezoelectric effects, the corresponding dynamic motion equation is established by using the Lagrange method with the assumed mode method. The flutter speed and frequency of the closed-loop system with time delay are obtained by solving a polynomial eigenvalue problem. An observer-based controller that does not dependent on time delay is developed for suppressing the flutter, and the corresponding gain matrices are obtained by solving linear matrix inequalities. The sufficient condition for the asymptotic stability of the closed-loop system is derived in terms of linear matrix inequalities. The simulation results demonstrate that the proposed control strategy based on the piezoelectric actuator is effective in wing bending-torsion coupling flutter system with a delayed output.</description><identifier>ISSN: 1077-5463</identifier><identifier>EISSN: 1741-2986</identifier><identifier>DOI: 10.1177/1077546320949122</identifier><language>eng</language><publisher>London, England: SAGE Publications</publisher><subject>Aerodynamics ; Aeroelasticity ; Algorithms ; Bending moments ; Closed loop systems ; Control algorithms ; Control theory ; Coupling ; Eigenvalues ; Equations of motion ; Feedback control ; Flutter ; Linear matrix inequalities ; Mathematical analysis ; Piezoelectric actuators ; Polynomials ; Sliding mode control ; Time dependence ; Time lag ; Vibration</subject><ispartof>Journal of vibration and control, 2021-08, Vol.27 (15-16), p.1824-1841</ispartof><rights>The Author(s) 2020</rights><lds50>peer_reviewed</lds50><woscitedreferencessubscribed>false</woscitedreferencessubscribed><citedby>FETCH-LOGICAL-c309t-3c9471f728d45495c72198090b1f18e34efe0da6313f7dc753b9f2e65de3bb6b3</citedby><cites>FETCH-LOGICAL-c309t-3c9471f728d45495c72198090b1f18e34efe0da6313f7dc753b9f2e65de3bb6b3</cites><orcidid>0000-0003-0885-7845 ; 0000-0002-9999-4820 ; 0000-0001-5394-7714 ; 0000-0001-7353-663X</orcidid></display><links><openurl>$$Topenurl_article</openurl><openurlfulltext>$$Topenurlfull_article</openurlfulltext><thumbnail>$$Tsyndetics_thumb_exl</thumbnail><link.rule.ids>314,780,784,27924,27925,79236</link.rule.ids></links><search><creatorcontrib>Li, Da</creatorcontrib><creatorcontrib>Yang, Hui</creatorcontrib><creatorcontrib>Qi, Na</creatorcontrib><creatorcontrib>Yuan, Jiaxin</creatorcontrib><title>Observer-based sliding mode control for piezoelectric wing bending-torsion coupling flutter involving delayed output</title><title>Journal of vibration and control</title><description>An observer-based sliding mode control scheme is proposed for suppressing bending-torsion coupling flutter motions of a wing aeroelastic system with delayed output by using the piezoelectric patch actuators. The wing structure is modeled as a thin-walled beam, and the aerodynamics on the wing are computed by the strip theory. For the implementation of the control algorithm, the piezoelectric patch is bonded on the top surface of the beam to act as the actuator. Ignoring the effect of piezoelectric actuators on structural dynamics, only considering the bending moments induced by piezoelectric effects, the corresponding dynamic motion equation is established by using the Lagrange method with the assumed mode method. The flutter speed and frequency of the closed-loop system with time delay are obtained by solving a polynomial eigenvalue problem. An observer-based controller that does not dependent on time delay is developed for suppressing the flutter, and the corresponding gain matrices are obtained by solving linear matrix inequalities. The sufficient condition for the asymptotic stability of the closed-loop system is derived in terms of linear matrix inequalities. The simulation results demonstrate that the proposed control strategy based on the piezoelectric actuator is effective in wing bending-torsion coupling flutter system with a delayed output.</description><subject>Aerodynamics</subject><subject>Aeroelasticity</subject><subject>Algorithms</subject><subject>Bending moments</subject><subject>Closed loop systems</subject><subject>Control algorithms</subject><subject>Control theory</subject><subject>Coupling</subject><subject>Eigenvalues</subject><subject>Equations of motion</subject><subject>Feedback control</subject><subject>Flutter</subject><subject>Linear matrix inequalities</subject><subject>Mathematical analysis</subject><subject>Piezoelectric actuators</subject><subject>Polynomials</subject><subject>Sliding mode control</subject><subject>Time dependence</subject><subject>Time lag</subject><subject>Vibration</subject><issn>1077-5463</issn><issn>1741-2986</issn><fulltext>true</fulltext><rsrctype>article</rsrctype><creationdate>2021</creationdate><recordtype>article</recordtype><recordid>eNp1kM1LxDAQxYMouK7ePRY8R_PVpjnK4hcIe9FzaZLJ0iXb1CRdWf96W1YQBE8zzPu9N_AQuqbkllIp7yiRshQVZ0QJRRk7QQsqBcVM1dXptE8ynvVzdJHSlhAiBCULlNc6QdxDxLpNYIvkO9v1m2IXLBQm9DkGX7gQi6GDrwAeTI6dKT5nRkM_sziHmLrQT_g4-FlwfswZYtH1--D388WCbw9TfBjzMOZLdOZan-DqZy7R--PD2-oZv66fXlb3r9hwojLmRglJnWS1FaVQpZGMqpoooqmjNXABDohtK065k9bIkmvlGFSlBa51pfkS3Rxzhxg-Rki52YYx9tPLhpVC1KzkjE8UOVImhpQiuGaI3a6Nh4aSZu62-dvtZMFHS2o38Bv6L_8NjH17Og</recordid><startdate>202108</startdate><enddate>202108</enddate><creator>Li, Da</creator><creator>Yang, Hui</creator><creator>Qi, Na</creator><creator>Yuan, Jiaxin</creator><general>SAGE Publications</general><general>SAGE PUBLICATIONS, INC</general><scope>AAYXX</scope><scope>CITATION</scope><scope>7SC</scope><scope>7SP</scope><scope>7TB</scope><scope>8FD</scope><scope>FR3</scope><scope>JQ2</scope><scope>KR7</scope><scope>L7M</scope><scope>L~C</scope><scope>L~D</scope><orcidid>https://orcid.org/0000-0003-0885-7845</orcidid><orcidid>https://orcid.org/0000-0002-9999-4820</orcidid><orcidid>https://orcid.org/0000-0001-5394-7714</orcidid><orcidid>https://orcid.org/0000-0001-7353-663X</orcidid></search><sort><creationdate>202108</creationdate><title>Observer-based sliding mode control for piezoelectric wing bending-torsion coupling flutter involving delayed output</title><author>Li, Da ; Yang, Hui ; Qi, Na ; Yuan, Jiaxin</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-LOGICAL-c309t-3c9471f728d45495c72198090b1f18e34efe0da6313f7dc753b9f2e65de3bb6b3</frbrgroupid><rsrctype>articles</rsrctype><prefilter>articles</prefilter><language>eng</language><creationdate>2021</creationdate><topic>Aerodynamics</topic><topic>Aeroelasticity</topic><topic>Algorithms</topic><topic>Bending moments</topic><topic>Closed loop systems</topic><topic>Control algorithms</topic><topic>Control theory</topic><topic>Coupling</topic><topic>Eigenvalues</topic><topic>Equations of motion</topic><topic>Feedback control</topic><topic>Flutter</topic><topic>Linear matrix inequalities</topic><topic>Mathematical analysis</topic><topic>Piezoelectric actuators</topic><topic>Polynomials</topic><topic>Sliding mode control</topic><topic>Time dependence</topic><topic>Time lag</topic><topic>Vibration</topic><toplevel>peer_reviewed</toplevel><toplevel>online_resources</toplevel><creatorcontrib>Li, Da</creatorcontrib><creatorcontrib>Yang, Hui</creatorcontrib><creatorcontrib>Qi, Na</creatorcontrib><creatorcontrib>Yuan, Jiaxin</creatorcontrib><collection>CrossRef</collection><collection>Computer and Information Systems Abstracts</collection><collection>Electronics & Communications Abstracts</collection><collection>Mechanical & Transportation Engineering Abstracts</collection><collection>Technology Research Database</collection><collection>Engineering Research Database</collection><collection>ProQuest Computer Science Collection</collection><collection>Civil Engineering Abstracts</collection><collection>Advanced Technologies Database with Aerospace</collection><collection>Computer and Information Systems Abstracts – Academic</collection><collection>Computer and Information Systems Abstracts Professional</collection><jtitle>Journal of vibration and control</jtitle></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext</fulltext></delivery><addata><au>Li, Da</au><au>Yang, Hui</au><au>Qi, Na</au><au>Yuan, Jiaxin</au><format>journal</format><genre>article</genre><ristype>JOUR</ristype><atitle>Observer-based sliding mode control for piezoelectric wing bending-torsion coupling flutter involving delayed output</atitle><jtitle>Journal of vibration and control</jtitle><date>2021-08</date><risdate>2021</risdate><volume>27</volume><issue>15-16</issue><spage>1824</spage><epage>1841</epage><pages>1824-1841</pages><issn>1077-5463</issn><eissn>1741-2986</eissn><abstract>An observer-based sliding mode control scheme is proposed for suppressing bending-torsion coupling flutter motions of a wing aeroelastic system with delayed output by using the piezoelectric patch actuators. The wing structure is modeled as a thin-walled beam, and the aerodynamics on the wing are computed by the strip theory. For the implementation of the control algorithm, the piezoelectric patch is bonded on the top surface of the beam to act as the actuator. Ignoring the effect of piezoelectric actuators on structural dynamics, only considering the bending moments induced by piezoelectric effects, the corresponding dynamic motion equation is established by using the Lagrange method with the assumed mode method. The flutter speed and frequency of the closed-loop system with time delay are obtained by solving a polynomial eigenvalue problem. An observer-based controller that does not dependent on time delay is developed for suppressing the flutter, and the corresponding gain matrices are obtained by solving linear matrix inequalities. The sufficient condition for the asymptotic stability of the closed-loop system is derived in terms of linear matrix inequalities. The simulation results demonstrate that the proposed control strategy based on the piezoelectric actuator is effective in wing bending-torsion coupling flutter system with a delayed output.</abstract><cop>London, England</cop><pub>SAGE Publications</pub><doi>10.1177/1077546320949122</doi><tpages>18</tpages><orcidid>https://orcid.org/0000-0003-0885-7845</orcidid><orcidid>https://orcid.org/0000-0002-9999-4820</orcidid><orcidid>https://orcid.org/0000-0001-5394-7714</orcidid><orcidid>https://orcid.org/0000-0001-7353-663X</orcidid></addata></record> |
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subjects | Aerodynamics Aeroelasticity Algorithms Bending moments Closed loop systems Control algorithms Control theory Coupling Eigenvalues Equations of motion Feedback control Flutter Linear matrix inequalities Mathematical analysis Piezoelectric actuators Polynomials Sliding mode control Time dependence Time lag Vibration |
title | Observer-based sliding mode control for piezoelectric wing bending-torsion coupling flutter involving delayed output |
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