Nonlinear optimum model following control of flexible aircraft.
Autor(a) principal: | |
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Data de Publicação: | 2010 |
Tipo de documento: | Tese |
Idioma: | eng |
Título da fonte: | Biblioteca Digital de Teses e Dissertações do ITA |
Texto Completo: | http://www.bd.bibl.ita.br/tde_busca/arquivo.php?codArquivo=1099 |
Resumo: | This Doctorate Thesis concerns optimum control of flexible aircraft. Models of a conceptual flexible aircraft are developed for control applications. A general model following problem via output feedback is developed and applied to the conceptual aircraft. The models are determined for 3 aircraft variants with increasing flexibility. The aerodynamics of flexible body is given by the Doublet Lattice method. The dynamics of the flexible structure is obtained via modal superposition. Controllability measures, given from control amplitude and rate constraints, are evaluated. Stabilization of flexible modes is performed via static output feedback. Control channels are defined with support of modal controllability and observability indexes. These applications contribute to determine the configuration of control surfaces. In order to treat the control of flexible aircraft, a rigid body approximation is proposed as the reference model. A general problem is posed, that consists in the determination of an optimum quadratic nonlinear output feedback for nonlinear plant and reference model, in order to approximate the input-output behavior of the reference model, for given performance outputs. Novel optimum and sub-optimum results, involving time variant and invariant linear state and output feedback and nonlinear time invariant output feedback, via neural networks, are developed. All these results are applied to the nonlinear model of conceptual aircraft and respective linear approximation, with comparisons among them. The efficiency and efficacy of the results are shown, and the importance of the nonlinear control is evidenced. |
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Biblioteca Digital de Teses e Dissertações do ITA |
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Nonlinear optimum model following control of flexible aircraft.Controle de aeronavesCorpos flexíveisControle adaptativo por modelo de referênciaControle ótimoSistemas não-linearesAerodinâmicaEngenharia aeronáuticaThis Doctorate Thesis concerns optimum control of flexible aircraft. Models of a conceptual flexible aircraft are developed for control applications. A general model following problem via output feedback is developed and applied to the conceptual aircraft. The models are determined for 3 aircraft variants with increasing flexibility. The aerodynamics of flexible body is given by the Doublet Lattice method. The dynamics of the flexible structure is obtained via modal superposition. Controllability measures, given from control amplitude and rate constraints, are evaluated. Stabilization of flexible modes is performed via static output feedback. Control channels are defined with support of modal controllability and observability indexes. These applications contribute to determine the configuration of control surfaces. In order to treat the control of flexible aircraft, a rigid body approximation is proposed as the reference model. A general problem is posed, that consists in the determination of an optimum quadratic nonlinear output feedback for nonlinear plant and reference model, in order to approximate the input-output behavior of the reference model, for given performance outputs. Novel optimum and sub-optimum results, involving time variant and invariant linear state and output feedback and nonlinear time invariant output feedback, via neural networks, are developed. All these results are applied to the nonlinear model of conceptual aircraft and respective linear approximation, with comparisons among them. The efficiency and efficacy of the results are shown, and the importance of the nonlinear control is evidenced.Instituto Tecnológico de AeronáuticaTakashi YoneyamaPedro PaglioneAndré Luís da Silva2010-12-10info:eu-repo/semantics/publishedVersioninfo:eu-repo/semantics/doctoralThesishttp://www.bd.bibl.ita.br/tde_busca/arquivo.php?codArquivo=1099reponame:Biblioteca Digital de Teses e Dissertações do ITAinstname:Instituto Tecnológico de Aeronáuticainstacron:ITAenginfo:eu-repo/semantics/openAccessapplication/pdf2019-02-02T14:02:34Zoai:agregador.ibict.br.BDTD_ITA:oai:ita.br:1099http://oai.bdtd.ibict.br/requestopendoar:null2020-05-28 19:35:16.73Biblioteca Digital de Teses e Dissertações do ITA - Instituto Tecnológico de Aeronáuticatrue |
dc.title.none.fl_str_mv |
Nonlinear optimum model following control of flexible aircraft. |
title |
Nonlinear optimum model following control of flexible aircraft. |
spellingShingle |
Nonlinear optimum model following control of flexible aircraft. André Luís da Silva Controle de aeronaves Corpos flexíveis Controle adaptativo por modelo de referência Controle ótimo Sistemas não-lineares Aerodinâmica Engenharia aeronáutica |
title_short |
Nonlinear optimum model following control of flexible aircraft. |
title_full |
Nonlinear optimum model following control of flexible aircraft. |
title_fullStr |
Nonlinear optimum model following control of flexible aircraft. |
title_full_unstemmed |
Nonlinear optimum model following control of flexible aircraft. |
title_sort |
Nonlinear optimum model following control of flexible aircraft. |
author |
André Luís da Silva |
author_facet |
André Luís da Silva |
author_role |
author |
dc.contributor.none.fl_str_mv |
Takashi Yoneyama Pedro Paglione |
dc.contributor.author.fl_str_mv |
André Luís da Silva |
dc.subject.por.fl_str_mv |
Controle de aeronaves Corpos flexíveis Controle adaptativo por modelo de referência Controle ótimo Sistemas não-lineares Aerodinâmica Engenharia aeronáutica |
topic |
Controle de aeronaves Corpos flexíveis Controle adaptativo por modelo de referência Controle ótimo Sistemas não-lineares Aerodinâmica Engenharia aeronáutica |
dc.description.none.fl_txt_mv |
This Doctorate Thesis concerns optimum control of flexible aircraft. Models of a conceptual flexible aircraft are developed for control applications. A general model following problem via output feedback is developed and applied to the conceptual aircraft. The models are determined for 3 aircraft variants with increasing flexibility. The aerodynamics of flexible body is given by the Doublet Lattice method. The dynamics of the flexible structure is obtained via modal superposition. Controllability measures, given from control amplitude and rate constraints, are evaluated. Stabilization of flexible modes is performed via static output feedback. Control channels are defined with support of modal controllability and observability indexes. These applications contribute to determine the configuration of control surfaces. In order to treat the control of flexible aircraft, a rigid body approximation is proposed as the reference model. A general problem is posed, that consists in the determination of an optimum quadratic nonlinear output feedback for nonlinear plant and reference model, in order to approximate the input-output behavior of the reference model, for given performance outputs. Novel optimum and sub-optimum results, involving time variant and invariant linear state and output feedback and nonlinear time invariant output feedback, via neural networks, are developed. All these results are applied to the nonlinear model of conceptual aircraft and respective linear approximation, with comparisons among them. The efficiency and efficacy of the results are shown, and the importance of the nonlinear control is evidenced. |
description |
This Doctorate Thesis concerns optimum control of flexible aircraft. Models of a conceptual flexible aircraft are developed for control applications. A general model following problem via output feedback is developed and applied to the conceptual aircraft. The models are determined for 3 aircraft variants with increasing flexibility. The aerodynamics of flexible body is given by the Doublet Lattice method. The dynamics of the flexible structure is obtained via modal superposition. Controllability measures, given from control amplitude and rate constraints, are evaluated. Stabilization of flexible modes is performed via static output feedback. Control channels are defined with support of modal controllability and observability indexes. These applications contribute to determine the configuration of control surfaces. In order to treat the control of flexible aircraft, a rigid body approximation is proposed as the reference model. A general problem is posed, that consists in the determination of an optimum quadratic nonlinear output feedback for nonlinear plant and reference model, in order to approximate the input-output behavior of the reference model, for given performance outputs. Novel optimum and sub-optimum results, involving time variant and invariant linear state and output feedback and nonlinear time invariant output feedback, via neural networks, are developed. All these results are applied to the nonlinear model of conceptual aircraft and respective linear approximation, with comparisons among them. The efficiency and efficacy of the results are shown, and the importance of the nonlinear control is evidenced. |
publishDate |
2010 |
dc.date.none.fl_str_mv |
2010-12-10 |
dc.type.driver.fl_str_mv |
info:eu-repo/semantics/publishedVersion info:eu-repo/semantics/doctoralThesis |
status_str |
publishedVersion |
format |
doctoralThesis |
dc.identifier.uri.fl_str_mv |
http://www.bd.bibl.ita.br/tde_busca/arquivo.php?codArquivo=1099 |
url |
http://www.bd.bibl.ita.br/tde_busca/arquivo.php?codArquivo=1099 |
dc.language.iso.fl_str_mv |
eng |
language |
eng |
dc.rights.driver.fl_str_mv |
info:eu-repo/semantics/openAccess |
eu_rights_str_mv |
openAccess |
dc.format.none.fl_str_mv |
application/pdf |
dc.publisher.none.fl_str_mv |
Instituto Tecnológico de Aeronáutica |
publisher.none.fl_str_mv |
Instituto Tecnológico de Aeronáutica |
dc.source.none.fl_str_mv |
reponame:Biblioteca Digital de Teses e Dissertações do ITA instname:Instituto Tecnológico de Aeronáutica instacron:ITA |
reponame_str |
Biblioteca Digital de Teses e Dissertações do ITA |
collection |
Biblioteca Digital de Teses e Dissertações do ITA |
instname_str |
Instituto Tecnológico de Aeronáutica |
instacron_str |
ITA |
institution |
ITA |
repository.name.fl_str_mv |
Biblioteca Digital de Teses e Dissertações do ITA - Instituto Tecnológico de Aeronáutica |
repository.mail.fl_str_mv |
|
subject_por_txtF_mv |
Controle de aeronaves Corpos flexíveis Controle adaptativo por modelo de referência Controle ótimo Sistemas não-lineares Aerodinâmica Engenharia aeronáutica |
_version_ |
1706809266238652416 |