Assessment of linearized buckling and nonlinear behavior of composite panels

Detalhes bibliográficos
Autor(a) principal: Luciano Alves Martins
Data de Publicação: 2009
Tipo de documento: Dissertação
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=1289
Resumo: A conventional approach to the computation of critical loads of structures is to linearize the prebuckling state and to solve the resulting eigenproblem in order to obtain buckling loads as well as buckling modes. However, this approach is flawed, or extremely misleading, if in reality the prebuckling state is far from linear. Simple and useful structures, such as composite flat and cylindrical panels, have their buckling loads computed by traditional methods (linearized buckling). Nonlinear approaches are subsequently used to evaluate how realistic those linearized buckling loads are. Different stacking sequences are assessed in order to try to obtain information regarding the quality or realism of the linearized buckling loads. It is observed that for some laminates linearizing the prebuckling state leads to reasonable results. However, for other stacking sequences the results can be substantially inaccurate.
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spelling Assessment of linearized buckling and nonlinear behavior of composite panelsFlambagemMateriais compósitosMétodo de elementos finitosLaminadosAnálise estruturalEngenharia de materiaisA conventional approach to the computation of critical loads of structures is to linearize the prebuckling state and to solve the resulting eigenproblem in order to obtain buckling loads as well as buckling modes. However, this approach is flawed, or extremely misleading, if in reality the prebuckling state is far from linear. Simple and useful structures, such as composite flat and cylindrical panels, have their buckling loads computed by traditional methods (linearized buckling). Nonlinear approaches are subsequently used to evaluate how realistic those linearized buckling loads are. Different stacking sequences are assessed in order to try to obtain information regarding the quality or realism of the linearized buckling loads. It is observed that for some laminates linearizing the prebuckling state leads to reasonable results. However, for other stacking sequences the results can be substantially inaccurate.Instituto Tecnológico de AeronáuticaAlfredo Rocha de FariaLuciano Alves Martins2009-10-29info:eu-repo/semantics/publishedVersioninfo:eu-repo/semantics/masterThesishttp://www.bd.bibl.ita.br/tde_busca/arquivo.php?codArquivo=1289reponame:Biblioteca Digital de Teses e Dissertações do ITAinstname:Instituto Tecnológico de Aeronáuticainstacron:ITAenginfo:eu-repo/semantics/openAccessapplication/pdf2019-02-02T14:02:37Zoai:agregador.ibict.br.BDTD_ITA:oai:ita.br:1289http://oai.bdtd.ibict.br/requestopendoar:null2020-05-28 19:35:58.099Biblioteca Digital de Teses e Dissertações do ITA - Instituto Tecnológico de Aeronáuticatrue
dc.title.none.fl_str_mv Assessment of linearized buckling and nonlinear behavior of composite panels
title Assessment of linearized buckling and nonlinear behavior of composite panels
spellingShingle Assessment of linearized buckling and nonlinear behavior of composite panels
Luciano Alves Martins
Flambagem
Materiais compósitos
Método de elementos finitos
Laminados
Análise estrutural
Engenharia de materiais
title_short Assessment of linearized buckling and nonlinear behavior of composite panels
title_full Assessment of linearized buckling and nonlinear behavior of composite panels
title_fullStr Assessment of linearized buckling and nonlinear behavior of composite panels
title_full_unstemmed Assessment of linearized buckling and nonlinear behavior of composite panels
title_sort Assessment of linearized buckling and nonlinear behavior of composite panels
author Luciano Alves Martins
author_facet Luciano Alves Martins
author_role author
dc.contributor.none.fl_str_mv Alfredo Rocha de Faria
dc.contributor.author.fl_str_mv Luciano Alves Martins
dc.subject.por.fl_str_mv Flambagem
Materiais compósitos
Método de elementos finitos
Laminados
Análise estrutural
Engenharia de materiais
topic Flambagem
Materiais compósitos
Método de elementos finitos
Laminados
Análise estrutural
Engenharia de materiais
dc.description.none.fl_txt_mv A conventional approach to the computation of critical loads of structures is to linearize the prebuckling state and to solve the resulting eigenproblem in order to obtain buckling loads as well as buckling modes. However, this approach is flawed, or extremely misleading, if in reality the prebuckling state is far from linear. Simple and useful structures, such as composite flat and cylindrical panels, have their buckling loads computed by traditional methods (linearized buckling). Nonlinear approaches are subsequently used to evaluate how realistic those linearized buckling loads are. Different stacking sequences are assessed in order to try to obtain information regarding the quality or realism of the linearized buckling loads. It is observed that for some laminates linearizing the prebuckling state leads to reasonable results. However, for other stacking sequences the results can be substantially inaccurate.
description A conventional approach to the computation of critical loads of structures is to linearize the prebuckling state and to solve the resulting eigenproblem in order to obtain buckling loads as well as buckling modes. However, this approach is flawed, or extremely misleading, if in reality the prebuckling state is far from linear. Simple and useful structures, such as composite flat and cylindrical panels, have their buckling loads computed by traditional methods (linearized buckling). Nonlinear approaches are subsequently used to evaluate how realistic those linearized buckling loads are. Different stacking sequences are assessed in order to try to obtain information regarding the quality or realism of the linearized buckling loads. It is observed that for some laminates linearizing the prebuckling state leads to reasonable results. However, for other stacking sequences the results can be substantially inaccurate.
publishDate 2009
dc.date.none.fl_str_mv 2009-10-29
dc.type.driver.fl_str_mv info:eu-repo/semantics/publishedVersion
info:eu-repo/semantics/masterThesis
status_str publishedVersion
format masterThesis
dc.identifier.uri.fl_str_mv http://www.bd.bibl.ita.br/tde_busca/arquivo.php?codArquivo=1289
url http://www.bd.bibl.ita.br/tde_busca/arquivo.php?codArquivo=1289
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 Flambagem
Materiais compósitos
Método de elementos finitos
Laminados
Análise estrutural
Engenharia de materiais
_version_ 1706809267651084288

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