Evaluation of laminated composite plates behavior under shear-after-impatc loading conditions: a methodology proposal

Detalhes bibliográficos
Ano de defesa: 2021
Autor(a) principal: Gabriel Sales Candido Souza
Orientador(a): Volnei Tita
Banca de defesa: Rui Jorge Sousa Costa de Miranda Guedes, Maikson Luiz Passaia Tonatto
Tipo de documento: Dissertação
Tipo de acesso: Acesso aberto
Idioma: eng
Instituição de defesa: Universidade de São Paulo
Programa de Pós-Graduação: Engenharia Mecânica
Departamento: Não Informado pela instituição
País: BR
Link de acesso: https://doi.org/10.11606/D.18.2021.tde-05082021-081042
Resumo: Fiber-reinforced polymer (FRP) laminated composite materials represents the greatest revolution since the development of the jet turbine in aeronautical industry. Possessing high stiffness and strength to weight ratio, they encounter increasingly space in high-performance applications, particularly in aircrafts. However, nowadays there are limitations in their usage attached to the complexity of prediction of behavior that these materials presents under impact loadings, which can result in a significant reduction in their mechanical properties. Moreover, due to its heterogeneity and anisotropy, the description of initiation and propagation of damage and failure mechanisms are not fully understood yet. Thus, the application of composite materials in aeronautical structures still follow conservative design philosophies. In this context, it is strategic the study of the mechanical behavior and the failure development and evolution presented by these materials. Following this, the post-failure behavior comprehension, in the sense of prediction of its residual strength, it is of major relevance to use damage tolerant design philosophies when designing one structure. So, this work presents a experimental approach, computationally aided, to evaluate the shear-after (low-velocity) impact behavior of FRP composites with unidirectional (UD) reinforcement since this is a poorly explored theme by the existent literature. Based on Continuum Damage Mechanics (CDM), a material model present in the literature is employed to investigate computationally the failure and post-failure of these materials under impact an shear-after-impact loadings. Thus, experimental tests in [0º]16 specimens are conducted in a 3-rail and drop-weight tests apparatus to obtain the stress-strain curves results for laminates with and without damage. Based in these, a phenomenological damage metric for shear-after-impact is proposed to aid the obtaining of the residual strength of these materials. Computational simulations are realized aiming to obtain, using the finite element method, the tendencies experimentally observed and to evaluate the potentialities and limitations of the material model employed. It is concluded at the end of this work that the proposed methodology is promising to obtain a complementary to the already consolidated approaches of compression- and flexure-after-impact.
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spelling info:eu-repo/semantics/publishedVersioninfo:eu-repo/semantics/masterThesis Evaluation of laminated composite plates behavior under shear-after-impatc loading conditions: a methodology proposal Avaliação do comportamento de placas laminadas de material compósito sob cisalhamento após carregamento de impacto 2021-02-26Volnei TitaRui Jorge Sousa Costa de Miranda GuedesMaikson Luiz Passaia TonattoGabriel Sales Candido SouzaUniversidade de São PauloEngenharia MecânicaUSPBR Análise de elementos finitos Carregamento de impacto Cisalhamento pós-impacto Comportamento pós-impacto Compósitos laminados Finite element analysis Impact loading Laminated composites Post-impact behavior Shear-after-impact Fiber-reinforced polymer (FRP) laminated composite materials represents the greatest revolution since the development of the jet turbine in aeronautical industry. Possessing high stiffness and strength to weight ratio, they encounter increasingly space in high-performance applications, particularly in aircrafts. However, nowadays there are limitations in their usage attached to the complexity of prediction of behavior that these materials presents under impact loadings, which can result in a significant reduction in their mechanical properties. Moreover, due to its heterogeneity and anisotropy, the description of initiation and propagation of damage and failure mechanisms are not fully understood yet. Thus, the application of composite materials in aeronautical structures still follow conservative design philosophies. In this context, it is strategic the study of the mechanical behavior and the failure development and evolution presented by these materials. Following this, the post-failure behavior comprehension, in the sense of prediction of its residual strength, it is of major relevance to use damage tolerant design philosophies when designing one structure. So, this work presents a experimental approach, computationally aided, to evaluate the shear-after (low-velocity) impact behavior of FRP composites with unidirectional (UD) reinforcement since this is a poorly explored theme by the existent literature. Based on Continuum Damage Mechanics (CDM), a material model present in the literature is employed to investigate computationally the failure and post-failure of these materials under impact an shear-after-impact loadings. Thus, experimental tests in [0º]16 specimens are conducted in a 3-rail and drop-weight tests apparatus to obtain the stress-strain curves results for laminates with and without damage. Based in these, a phenomenological damage metric for shear-after-impact is proposed to aid the obtaining of the residual strength of these materials. Computational simulations are realized aiming to obtain, using the finite element method, the tendencies experimentally observed and to evaluate the potentialities and limitations of the material model employed. It is concluded at the end of this work that the proposed methodology is promising to obtain a complementary to the already consolidated approaches of compression- and flexure-after-impact. Materiais compósitos laminados de matriz polimérica reforçados por fibras (MPRF) representam, na indústria aeronáutica, a maior revolução desde o advento da turbina a jato. Possuindo alta rigidez e resistência específica, estes encontram cada vez mais espaço em aplicações de alta performance e, especialmente, em aeronaves. Contudo, atualmente existem limitações em seu uso atreladas a complexidade na previsão do comportamento destes materiais sob carregamentos de impacto, o qual pode resultar em redução significativa em suas propriedades mecânicas. Além disso, devido a sua heterogeneidade e anisotropia, os mecanismos de iniciação e progressão de dano e falha não são entendidos plenamente. Desta forma, a aplicação de materiais compósitos em estruturas aeronáuticas ainda seguem filosofias de projeto conservadoras. Neste contexto, é estratégico o estudo do comportamento mecânico e do processo de falha apresentado por estes materiais. Além disso, o comportamento pós-falha, no sentido de prever sua resistência residual, é de grande importância para utilização de filosofias tolerantes ao dano ao se projetar uma dada estrutura. Assim, este trabalho apresenta uma abordagem experimental, auxiliada computacionalmente, para avaliar o comportamento de compósitos do tipo MPRF sob cisalhamento pós-impacto de baixa velocidade com reforço unidirecional tendo em vista que este é um tema pouco explorado pela literatura existente. Com base na Mecânica do Dano Contínuo, emprega-se um modelo de material da literatura afim de se investigar computacionalmente a falha e pós-falha destes materiais sob impacto e cisalhamento pós-impacto. Assim, ensaios experimentais em espécimes [0º]16 são conduzidos em um aparato de rail test (3 trilhos) e drop test a fim de se obter resultados de curvas tensão-deformação para os laminados com e sem dano. Baseado nestes, uma métrica de dano fenomenológica para cisalhamento pós-impacto é proposta para auxiliar na obtenção da resistência residual destes materiais. Simulações computacionais são realizadas afim de se obter via método dos elementos finitos as tendências observadas experimentalmente e para avaliar as potencialidades e limitações do modelo de material utilizado. Conclui-se ao término deste trabalho que a metodologia proposta é promissora para se obter um complementar as abordagens já consolidadas de compressão e flexão pós-impacto. https://doi.org/10.11606/D.18.2021.tde-05082021-081042info:eu-repo/semantics/openAccessengreponame:Biblioteca Digital de Teses e Dissertações da USPinstname:Universidade de São Paulo (USP)instacron:USP2023-12-21T18:16:29Zoai:teses.usp.br:tde-05082021-081042Biblioteca Digital de Teses e Dissertaçõeshttp://www.teses.usp.br/PUBhttp://www.teses.usp.br/cgi-bin/mtd2br.plvirginia@if.usp.br|| atendimento@aguia.usp.br||virginia@if.usp.bropendoar:27212021-08-09T21:15:02Biblioteca Digital de Teses e Dissertações da USP - Universidade de São Paulo (USP)false
dc.title.en.fl_str_mv Evaluation of laminated composite plates behavior under shear-after-impatc loading conditions: a methodology proposal
dc.title.alternative.pt.fl_str_mv Avaliação do comportamento de placas laminadas de material compósito sob cisalhamento após carregamento de impacto
title Evaluation of laminated composite plates behavior under shear-after-impatc loading conditions: a methodology proposal
spellingShingle Evaluation of laminated composite plates behavior under shear-after-impatc loading conditions: a methodology proposal
Gabriel Sales Candido Souza
title_short Evaluation of laminated composite plates behavior under shear-after-impatc loading conditions: a methodology proposal
title_full Evaluation of laminated composite plates behavior under shear-after-impatc loading conditions: a methodology proposal
title_fullStr Evaluation of laminated composite plates behavior under shear-after-impatc loading conditions: a methodology proposal
title_full_unstemmed Evaluation of laminated composite plates behavior under shear-after-impatc loading conditions: a methodology proposal
title_sort Evaluation of laminated composite plates behavior under shear-after-impatc loading conditions: a methodology proposal
author Gabriel Sales Candido Souza
author_facet Gabriel Sales Candido Souza
author_role author
dc.contributor.advisor1.fl_str_mv Volnei Tita
dc.contributor.referee1.fl_str_mv Rui Jorge Sousa Costa de Miranda Guedes
dc.contributor.referee2.fl_str_mv Maikson Luiz Passaia Tonatto
dc.contributor.author.fl_str_mv Gabriel Sales Candido Souza
contributor_str_mv Volnei Tita
Rui Jorge Sousa Costa de Miranda Guedes
Maikson Luiz Passaia Tonatto
description Fiber-reinforced polymer (FRP) laminated composite materials represents the greatest revolution since the development of the jet turbine in aeronautical industry. Possessing high stiffness and strength to weight ratio, they encounter increasingly space in high-performance applications, particularly in aircrafts. However, nowadays there are limitations in their usage attached to the complexity of prediction of behavior that these materials presents under impact loadings, which can result in a significant reduction in their mechanical properties. Moreover, due to its heterogeneity and anisotropy, the description of initiation and propagation of damage and failure mechanisms are not fully understood yet. Thus, the application of composite materials in aeronautical structures still follow conservative design philosophies. In this context, it is strategic the study of the mechanical behavior and the failure development and evolution presented by these materials. Following this, the post-failure behavior comprehension, in the sense of prediction of its residual strength, it is of major relevance to use damage tolerant design philosophies when designing one structure. So, this work presents a experimental approach, computationally aided, to evaluate the shear-after (low-velocity) impact behavior of FRP composites with unidirectional (UD) reinforcement since this is a poorly explored theme by the existent literature. Based on Continuum Damage Mechanics (CDM), a material model present in the literature is employed to investigate computationally the failure and post-failure of these materials under impact an shear-after-impact loadings. Thus, experimental tests in [0º]16 specimens are conducted in a 3-rail and drop-weight tests apparatus to obtain the stress-strain curves results for laminates with and without damage. Based in these, a phenomenological damage metric for shear-after-impact is proposed to aid the obtaining of the residual strength of these materials. Computational simulations are realized aiming to obtain, using the finite element method, the tendencies experimentally observed and to evaluate the potentialities and limitations of the material model employed. It is concluded at the end of this work that the proposed methodology is promising to obtain a complementary to the already consolidated approaches of compression- and flexure-after-impact.
publishDate 2021
dc.date.issued.fl_str_mv 2021-02-26
dc.type.status.fl_str_mv info:eu-repo/semantics/publishedVersion
dc.type.driver.fl_str_mv info:eu-repo/semantics/masterThesis
format masterThesis
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dc.identifier.uri.fl_str_mv https://doi.org/10.11606/D.18.2021.tde-05082021-081042
url https://doi.org/10.11606/D.18.2021.tde-05082021-081042
dc.language.iso.fl_str_mv eng
language eng
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dc.publisher.none.fl_str_mv Universidade de São Paulo
dc.publisher.program.fl_str_mv Engenharia Mecânica
dc.publisher.initials.fl_str_mv USP
dc.publisher.country.fl_str_mv BR
publisher.none.fl_str_mv Universidade de São Paulo
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