Control of Limit Cycle Oscillation in a Three Degrees of Freedom Airfoil Section Using Fuzzy Takagi-Sugeno Modeling

Detalhes bibliográficos
Autor(a) principal: Bueno, Douglas Domingues
Data de Publicação: 2014
Outros Autores: Sandoval Goes, Luiz Carlos, Paupitz Goncalves, Paulo Jose [UNESP]
Tipo de documento: Artigo
Idioma: eng
Título da fonte: Repositório Institucional da UNESP
Texto Completo: http://dx.doi.org/10.1155/2014/597827
http://hdl.handle.net/11449/112050
Resumo: This work presents a strategy to control nonlinear responses of aeroelastic systems with control surface freeplay. The proposed methodology is developed for the three degrees of freedom typical section airfoil considering aerodynamic forces from Theodorsen's theory. The mathematical model is written in the state space representation using rational function approximation to write the aerodynamic forces in time domain. The control system is designed using the fuzzy Takagi-Sugeno modeling to compute a feedback control gain. It useds Lyapunov's stability function and linear matrix inequalities (LMIs) to solve a convex optimization problem. Time simulations with different initial conditions are performed using a modified Runge-Kutta algorithm to compare the system with and without control forces. It is shown that this approach can compute linear control gain able to stabilize aeroelastic systems with discontinuous nonlinearities.
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spelling Control of Limit Cycle Oscillation in a Three Degrees of Freedom Airfoil Section Using Fuzzy Takagi-Sugeno ModelingThis work presents a strategy to control nonlinear responses of aeroelastic systems with control surface freeplay. The proposed methodology is developed for the three degrees of freedom typical section airfoil considering aerodynamic forces from Theodorsen's theory. The mathematical model is written in the state space representation using rational function approximation to write the aerodynamic forces in time domain. The control system is designed using the fuzzy Takagi-Sugeno modeling to compute a feedback control gain. It useds Lyapunov's stability function and linear matrix inequalities (LMIs) to solve a convex optimization problem. Time simulations with different initial conditions are performed using a modified Runge-Kutta algorithm to compare the system with and without control forces. It is shown that this approach can compute linear control gain able to stabilize aeroelastic systems with discontinuous nonlinearities.Aeronaut Inst Technol ITA, BR-12228900 Sao Jose Dos Campos, SP, BrazilUniv Estadual Paulista UNESP, BR-17033360 Bauru, SP, BrazilUniv Estadual Paulista UNESP, BR-17033360 Bauru, SP, BrazilHindawi Publishing CorporationInstituto Tecnológico de Aeronáutica (ITA)Universidade Estadual Paulista (Unesp)Bueno, Douglas DominguesSandoval Goes, Luiz CarlosPaupitz Goncalves, Paulo Jose [UNESP]2014-12-03T13:09:11Z2014-12-03T13:09:11Z2014-01-01info:eu-repo/semantics/publishedVersioninfo:eu-repo/semantics/article12application/pdfhttp://dx.doi.org/10.1155/2014/597827Shock And Vibration. New York: Hindawi Publishing Corporation, 12 p., 2014.1070-9622http://hdl.handle.net/11449/11205010.1155/2014/597827WOS:000337837400001WOS000337837400001.pdfWeb of Sciencereponame:Repositório Institucional da UNESPinstname:Universidade Estadual Paulista (UNESP)instacron:UNESPengShock and Vibration1.8570,468info:eu-repo/semantics/openAccess2024-06-13T19:29:26Zoai:repositorio.unesp.br:11449/112050Repositório InstitucionalPUBhttp://repositorio.unesp.br/oai/requestopendoar:29462024-08-05T23:58:12.643459Repositório Institucional da UNESP - Universidade Estadual Paulista (UNESP)false
dc.title.none.fl_str_mv Control of Limit Cycle Oscillation in a Three Degrees of Freedom Airfoil Section Using Fuzzy Takagi-Sugeno Modeling
title Control of Limit Cycle Oscillation in a Three Degrees of Freedom Airfoil Section Using Fuzzy Takagi-Sugeno Modeling
spellingShingle Control of Limit Cycle Oscillation in a Three Degrees of Freedom Airfoil Section Using Fuzzy Takagi-Sugeno Modeling
Bueno, Douglas Domingues
title_short Control of Limit Cycle Oscillation in a Three Degrees of Freedom Airfoil Section Using Fuzzy Takagi-Sugeno Modeling
title_full Control of Limit Cycle Oscillation in a Three Degrees of Freedom Airfoil Section Using Fuzzy Takagi-Sugeno Modeling
title_fullStr Control of Limit Cycle Oscillation in a Three Degrees of Freedom Airfoil Section Using Fuzzy Takagi-Sugeno Modeling
title_full_unstemmed Control of Limit Cycle Oscillation in a Three Degrees of Freedom Airfoil Section Using Fuzzy Takagi-Sugeno Modeling
title_sort Control of Limit Cycle Oscillation in a Three Degrees of Freedom Airfoil Section Using Fuzzy Takagi-Sugeno Modeling
author Bueno, Douglas Domingues
author_facet Bueno, Douglas Domingues
Sandoval Goes, Luiz Carlos
Paupitz Goncalves, Paulo Jose [UNESP]
author_role author
author2 Sandoval Goes, Luiz Carlos
Paupitz Goncalves, Paulo Jose [UNESP]
author2_role author
author
dc.contributor.none.fl_str_mv Instituto Tecnológico de Aeronáutica (ITA)
Universidade Estadual Paulista (Unesp)
dc.contributor.author.fl_str_mv Bueno, Douglas Domingues
Sandoval Goes, Luiz Carlos
Paupitz Goncalves, Paulo Jose [UNESP]
description This work presents a strategy to control nonlinear responses of aeroelastic systems with control surface freeplay. The proposed methodology is developed for the three degrees of freedom typical section airfoil considering aerodynamic forces from Theodorsen's theory. The mathematical model is written in the state space representation using rational function approximation to write the aerodynamic forces in time domain. The control system is designed using the fuzzy Takagi-Sugeno modeling to compute a feedback control gain. It useds Lyapunov's stability function and linear matrix inequalities (LMIs) to solve a convex optimization problem. Time simulations with different initial conditions are performed using a modified Runge-Kutta algorithm to compare the system with and without control forces. It is shown that this approach can compute linear control gain able to stabilize aeroelastic systems with discontinuous nonlinearities.
publishDate 2014
dc.date.none.fl_str_mv 2014-12-03T13:09:11Z
2014-12-03T13:09:11Z
2014-01-01
dc.type.status.fl_str_mv info:eu-repo/semantics/publishedVersion
dc.type.driver.fl_str_mv info:eu-repo/semantics/article
format article
status_str publishedVersion
dc.identifier.uri.fl_str_mv http://dx.doi.org/10.1155/2014/597827
Shock And Vibration. New York: Hindawi Publishing Corporation, 12 p., 2014.
1070-9622
http://hdl.handle.net/11449/112050
10.1155/2014/597827
WOS:000337837400001
WOS000337837400001.pdf
url http://dx.doi.org/10.1155/2014/597827
http://hdl.handle.net/11449/112050
identifier_str_mv Shock And Vibration. New York: Hindawi Publishing Corporation, 12 p., 2014.
1070-9622
10.1155/2014/597827
WOS:000337837400001
WOS000337837400001.pdf
dc.language.iso.fl_str_mv eng
language eng
dc.relation.none.fl_str_mv Shock and Vibration
1.857
0,468
dc.rights.driver.fl_str_mv info:eu-repo/semantics/openAccess
eu_rights_str_mv openAccess
dc.format.none.fl_str_mv 12
application/pdf
dc.publisher.none.fl_str_mv Hindawi Publishing Corporation
publisher.none.fl_str_mv Hindawi Publishing Corporation
dc.source.none.fl_str_mv Web of Science
reponame:Repositório Institucional da UNESP
instname:Universidade Estadual Paulista (UNESP)
instacron:UNESP
instname_str Universidade Estadual Paulista (UNESP)
instacron_str UNESP
institution UNESP
reponame_str Repositório Institucional da UNESP
collection Repositório Institucional da UNESP
repository.name.fl_str_mv Repositório Institucional da UNESP - Universidade Estadual Paulista (UNESP)
repository.mail.fl_str_mv
_version_ 1808129568037404672

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