Nonlinear reduced-order modeling and bifurcation analysis of whirl flutter in a rotor-nacelle system
Autor(a) principal: | |
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Data de Publicação: | 2020 |
Outros Autores: | , , |
Tipo de documento: | Artigo de conferência |
Idioma: | eng |
Título da fonte: | Repositório Institucional da UNESP |
Texto Completo: | http://dx.doi.org/10.2514/6.2020-3181 http://hdl.handle.net/11449/205336 |
Resumo: | Whirl flutter is an aeroelastic instability that can be affected by structural or/and aerodynamic nonlinearities. This instability may lead to potentially dangerous behaviors. In this study, a nonlinear reduced-order model for a nacelle-rotor system, considering quasi-steady aerodynamics is implemented. First, a parametric study for the linear system is performed to determine the main aerodynamic and structural characteristics that affect the onset of instability. Multiple polynomial nonlinearities in the two degrees-of-freedom nacelle-rotor model are tested to simulate possible structural nonlinear effects including symmetric cubic hardening nonlinearities for the pitch and yaw degrees of freedom, purely yaw nonlinearity, purely pitch nonlinearity, and a combination of quadratic and cubic nonlinearities for both degrees of freedom. Preliminary results show that the presence of hardening structural nonlinearities introduces limit cycle oscillations to the system in the post-flutter regime. Moreover, the inclusion of quadratic nonlinearity introduces asymmetric oscillations and subcritical Hopf bifurcation. |
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Repositório Institucional da UNESP |
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spelling |
Nonlinear reduced-order modeling and bifurcation analysis of whirl flutter in a rotor-nacelle systemWhirl flutter is an aeroelastic instability that can be affected by structural or/and aerodynamic nonlinearities. This instability may lead to potentially dangerous behaviors. In this study, a nonlinear reduced-order model for a nacelle-rotor system, considering quasi-steady aerodynamics is implemented. First, a parametric study for the linear system is performed to determine the main aerodynamic and structural characteristics that affect the onset of instability. Multiple polynomial nonlinearities in the two degrees-of-freedom nacelle-rotor model are tested to simulate possible structural nonlinear effects including symmetric cubic hardening nonlinearities for the pitch and yaw degrees of freedom, purely yaw nonlinearity, purely pitch nonlinearity, and a combination of quadratic and cubic nonlinearities for both degrees of freedom. Preliminary results show that the presence of hardening structural nonlinearities introduces limit cycle oscillations to the system in the post-flutter regime. Moreover, the inclusion of quadratic nonlinearity introduces asymmetric oscillations and subcritical Hopf bifurcation.Department of Mechanical and Aerospace Engineering New Mexico State UniversitySao Paulo State University (UNESP)Sao Paulo State University (UNESP)New Mexico State UniversityUniversidade Estadual Paulista (Unesp)Quintana, A.Vasconcellos, R. [UNESP]Throneberry, G.Abdelkefi, A.2021-06-25T10:13:40Z2021-06-25T10:13:40Z2020-01-01info:eu-repo/semantics/publishedVersioninfo:eu-repo/semantics/conferenceObject1-9http://dx.doi.org/10.2514/6.2020-3181AIAA AVIATION 2020 FORUM, v. 1 PartF, p. 1-9.http://hdl.handle.net/11449/20533610.2514/6.2020-31812-s2.0-85092788116Scopusreponame:Repositório Institucional da UNESPinstname:Universidade Estadual Paulista (UNESP)instacron:UNESPengAIAA AVIATION 2020 FORUMinfo:eu-repo/semantics/openAccess2021-10-23T12:39:35Zoai:repositorio.unesp.br:11449/205336Repositório InstitucionalPUBhttp://repositorio.unesp.br/oai/requestopendoar:29462024-08-05T13:41:25.877515Repositório Institucional da UNESP - Universidade Estadual Paulista (UNESP)false |
dc.title.none.fl_str_mv |
Nonlinear reduced-order modeling and bifurcation analysis of whirl flutter in a rotor-nacelle system |
title |
Nonlinear reduced-order modeling and bifurcation analysis of whirl flutter in a rotor-nacelle system |
spellingShingle |
Nonlinear reduced-order modeling and bifurcation analysis of whirl flutter in a rotor-nacelle system Quintana, A. |
title_short |
Nonlinear reduced-order modeling and bifurcation analysis of whirl flutter in a rotor-nacelle system |
title_full |
Nonlinear reduced-order modeling and bifurcation analysis of whirl flutter in a rotor-nacelle system |
title_fullStr |
Nonlinear reduced-order modeling and bifurcation analysis of whirl flutter in a rotor-nacelle system |
title_full_unstemmed |
Nonlinear reduced-order modeling and bifurcation analysis of whirl flutter in a rotor-nacelle system |
title_sort |
Nonlinear reduced-order modeling and bifurcation analysis of whirl flutter in a rotor-nacelle system |
author |
Quintana, A. |
author_facet |
Quintana, A. Vasconcellos, R. [UNESP] Throneberry, G. Abdelkefi, A. |
author_role |
author |
author2 |
Vasconcellos, R. [UNESP] Throneberry, G. Abdelkefi, A. |
author2_role |
author author author |
dc.contributor.none.fl_str_mv |
New Mexico State University Universidade Estadual Paulista (Unesp) |
dc.contributor.author.fl_str_mv |
Quintana, A. Vasconcellos, R. [UNESP] Throneberry, G. Abdelkefi, A. |
description |
Whirl flutter is an aeroelastic instability that can be affected by structural or/and aerodynamic nonlinearities. This instability may lead to potentially dangerous behaviors. In this study, a nonlinear reduced-order model for a nacelle-rotor system, considering quasi-steady aerodynamics is implemented. First, a parametric study for the linear system is performed to determine the main aerodynamic and structural characteristics that affect the onset of instability. Multiple polynomial nonlinearities in the two degrees-of-freedom nacelle-rotor model are tested to simulate possible structural nonlinear effects including symmetric cubic hardening nonlinearities for the pitch and yaw degrees of freedom, purely yaw nonlinearity, purely pitch nonlinearity, and a combination of quadratic and cubic nonlinearities for both degrees of freedom. Preliminary results show that the presence of hardening structural nonlinearities introduces limit cycle oscillations to the system in the post-flutter regime. Moreover, the inclusion of quadratic nonlinearity introduces asymmetric oscillations and subcritical Hopf bifurcation. |
publishDate |
2020 |
dc.date.none.fl_str_mv |
2020-01-01 2021-06-25T10:13:40Z 2021-06-25T10:13:40Z |
dc.type.status.fl_str_mv |
info:eu-repo/semantics/publishedVersion |
dc.type.driver.fl_str_mv |
info:eu-repo/semantics/conferenceObject |
format |
conferenceObject |
status_str |
publishedVersion |
dc.identifier.uri.fl_str_mv |
http://dx.doi.org/10.2514/6.2020-3181 AIAA AVIATION 2020 FORUM, v. 1 PartF, p. 1-9. http://hdl.handle.net/11449/205336 10.2514/6.2020-3181 2-s2.0-85092788116 |
url |
http://dx.doi.org/10.2514/6.2020-3181 http://hdl.handle.net/11449/205336 |
identifier_str_mv |
AIAA AVIATION 2020 FORUM, v. 1 PartF, p. 1-9. 10.2514/6.2020-3181 2-s2.0-85092788116 |
dc.language.iso.fl_str_mv |
eng |
language |
eng |
dc.relation.none.fl_str_mv |
AIAA AVIATION 2020 FORUM |
dc.rights.driver.fl_str_mv |
info:eu-repo/semantics/openAccess |
eu_rights_str_mv |
openAccess |
dc.format.none.fl_str_mv |
1-9 |
dc.source.none.fl_str_mv |
Scopus 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 |
|
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1808128265819258880 |