A thermal management system parametric model for fuel cell powered aircraft conceptual design

Detalhes bibliográficos
Ano de defesa: 2024
Autor(a) principal: Collares, Rodolfo da Silva
Orientador(a): Não Informado pela instituição
Banca de defesa: Não Informado pela instituição
Tipo de documento: Dissertação
Tipo de acesso: Acesso aberto
Idioma: eng
Instituição de defesa: Biblioteca Digitais de Teses e Dissertações da USP
Programa de Pós-Graduação: Não Informado pela instituição
Departamento: Não Informado pela instituição
País: Não Informado pela instituição
Palavras-chave em Português:
Link de acesso: https://www.teses.usp.br/teses/disponiveis/18/18161/tde-09092024-155909/
Resumo: It is a widely accepted fact that the world ambient temperature is rising, and it is correlated with the CO2 emissions produced by economic sectors such as energy, industry and transports. Aerospace segment has an important contribution to the CO2 emissions, therefore it studies solutions to reduce or eliminate it from its products. The studies include the replacement of fossil fuel aeronautical engines per Fuel Cells, which are devices that operate with hydrogen and produce electrical energy, water, and heat. Since fuel cells release considerable amount of heat, it requires a substantial TMS (thermal management system), which impacts the airplane weight and drag. Studies of fuel cell powered aircraft have been published, and the TMS is not neglected, but a deep discussion regarding its weight and drag estimation was not found. The present work develops a TMS weight and drag parametric model for fuel cell powered aircraft conceptual design, based on fuel cell and radiators physical models, and representing an optimum compromise between weight and drag. The work reveals linear correlation between the TMS parameters and fuel cell power. Significant dependence on fuel cell temperature has also been shown, therefore, three temperature levels were tested. It has also been observed that optimum solutions tend to require too large radiators, difficult to install, so, a limitation was inserted in the optimization cycle and models for three different area limits were generated. Then, regression equations have been determined to correlate the TMS parameters with fuel cell power, for various combinations of fuel cell operating temperature and radiator area limits, accomplishing the purpose of the work. It is recommended, for future works, the conduction of studies to investigate more efficient radiators, heat enhancement devices and TMS large radiators installation solutions.
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spelling A thermal management system parametric model for fuel cell powered aircraft conceptual designUm modelo paramétrico de sistema de gerenciamento térmico para projeto conceitual de aeronaves movidas a célula de combustívelaeronaves híbridasaircraft concept studiesaviação sustentávelcélula de combustívelefeito Meredithestudos conceituais de aeronavesfuel cellgerenciamento térmicohybrid-electric aircraftMeredith effectsustainable aviationthermal management systemIt is a widely accepted fact that the world ambient temperature is rising, and it is correlated with the CO2 emissions produced by economic sectors such as energy, industry and transports. Aerospace segment has an important contribution to the CO2 emissions, therefore it studies solutions to reduce or eliminate it from its products. The studies include the replacement of fossil fuel aeronautical engines per Fuel Cells, which are devices that operate with hydrogen and produce electrical energy, water, and heat. Since fuel cells release considerable amount of heat, it requires a substantial TMS (thermal management system), which impacts the airplane weight and drag. Studies of fuel cell powered aircraft have been published, and the TMS is not neglected, but a deep discussion regarding its weight and drag estimation was not found. The present work develops a TMS weight and drag parametric model for fuel cell powered aircraft conceptual design, based on fuel cell and radiators physical models, and representing an optimum compromise between weight and drag. The work reveals linear correlation between the TMS parameters and fuel cell power. Significant dependence on fuel cell temperature has also been shown, therefore, three temperature levels were tested. It has also been observed that optimum solutions tend to require too large radiators, difficult to install, so, a limitation was inserted in the optimization cycle and models for three different area limits were generated. Then, regression equations have been determined to correlate the TMS parameters with fuel cell power, for various combinations of fuel cell operating temperature and radiator area limits, accomplishing the purpose of the work. It is recommended, for future works, the conduction of studies to investigate more efficient radiators, heat enhancement devices and TMS large radiators installation solutions.É fato reconhecido que a temperatura ambiente da Terra está aumentando e isso está associado às emissões de CO2 provenientes de segmentos como energia, indústria e transportes. O setor aeroespacial responde por uma parcela dessas emissões, por isso pesquisa produtos para reduzi-las ou eliminá-las. Estudos incluem a viabilidade de substituir os motores a combustão por células de combustível, que consomem hidrogênio, produzindo eletricidade, água e calor. Por gerarem alta taxa de calor, esses equipamentos requerem um substancial SGT (sistema de gerenciamento térmico), que afeta o peso e arrasto da aeronave. Muitos estudos de aeronaves com célula de combustível foram publicados, e o SGT não foi ignorado, mas uma discussão dedicada a estimar seu peso e arrasto não foi encontrada. Este trabalho cria um modelo paramétrico de peso e arrasto de SGT de células de combustível para estudos conceituais de aeronaves, baseado em modelos físicos de células de combustível e radiadores, e representando o ponto ótimo entre peso e arrasto. O trabalho mostrou correlação linear entre os parâmetros do SGT e a potência da célula. Foi observada uma dependência desses parâmetros com a temperatura de operação da célula, então três temperaturas foram testadas. Observou-se que soluções ótimas requerem um SGT de grandes dimensões, de difícil instalação, então uma limitação foi inserida no ciclo de otimização e três limites de área foram testados. Regressões lineares foram, então, criadas correlacionando os parâmetros do SGT com a potência da célula, para diversas combinações de temperatura de operação e limite de área, cumprindo, assim, o propósito do trabalho. Recomenda-se, para trabalhos futuros, a condução de investigações de radiadores mais eficientes, técnicas de aumento de efetividade de troca de calor e soluções de instalação de radiadores de grandes dimensões.Biblioteca Digitais de Teses e Dissertações da USPBidinotto, Jorge HenriqueCollares, Rodolfo da Silva2024-08-09info:eu-repo/semantics/publishedVersioninfo:eu-repo/semantics/masterThesisapplication/pdfhttps://www.teses.usp.br/teses/disponiveis/18/18161/tde-09092024-155909/reponame:Biblioteca Digital de Teses e Dissertações da USPinstname:Universidade de São Paulo (USP)instacron:USPLiberar o conteúdo para acesso público.info:eu-repo/semantics/openAccesseng2024-09-11T13:22:02Zoai:teses.usp.br:tde-09092024-155909Biblioteca 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:27212024-09-11T13:22:02Biblioteca Digital de Teses e Dissertações da USP - Universidade de São Paulo (USP)false
dc.title.none.fl_str_mv A thermal management system parametric model for fuel cell powered aircraft conceptual design
Um modelo paramétrico de sistema de gerenciamento térmico para projeto conceitual de aeronaves movidas a célula de combustível
title A thermal management system parametric model for fuel cell powered aircraft conceptual design
spellingShingle A thermal management system parametric model for fuel cell powered aircraft conceptual design
Collares, Rodolfo da Silva
aeronaves híbridas
aircraft concept studies
aviação sustentável
célula de combustível
efeito Meredith
estudos conceituais de aeronaves
fuel cell
gerenciamento térmico
hybrid-electric aircraft
Meredith effect
sustainable aviation
thermal management system
title_short A thermal management system parametric model for fuel cell powered aircraft conceptual design
title_full A thermal management system parametric model for fuel cell powered aircraft conceptual design
title_fullStr A thermal management system parametric model for fuel cell powered aircraft conceptual design
title_full_unstemmed A thermal management system parametric model for fuel cell powered aircraft conceptual design
title_sort A thermal management system parametric model for fuel cell powered aircraft conceptual design
author Collares, Rodolfo da Silva
author_facet Collares, Rodolfo da Silva
author_role author
dc.contributor.none.fl_str_mv Bidinotto, Jorge Henrique
dc.contributor.author.fl_str_mv Collares, Rodolfo da Silva
dc.subject.por.fl_str_mv aeronaves híbridas
aircraft concept studies
aviação sustentável
célula de combustível
efeito Meredith
estudos conceituais de aeronaves
fuel cell
gerenciamento térmico
hybrid-electric aircraft
Meredith effect
sustainable aviation
thermal management system
topic aeronaves híbridas
aircraft concept studies
aviação sustentável
célula de combustível
efeito Meredith
estudos conceituais de aeronaves
fuel cell
gerenciamento térmico
hybrid-electric aircraft
Meredith effect
sustainable aviation
thermal management system
description It is a widely accepted fact that the world ambient temperature is rising, and it is correlated with the CO2 emissions produced by economic sectors such as energy, industry and transports. Aerospace segment has an important contribution to the CO2 emissions, therefore it studies solutions to reduce or eliminate it from its products. The studies include the replacement of fossil fuel aeronautical engines per Fuel Cells, which are devices that operate with hydrogen and produce electrical energy, water, and heat. Since fuel cells release considerable amount of heat, it requires a substantial TMS (thermal management system), which impacts the airplane weight and drag. Studies of fuel cell powered aircraft have been published, and the TMS is not neglected, but a deep discussion regarding its weight and drag estimation was not found. The present work develops a TMS weight and drag parametric model for fuel cell powered aircraft conceptual design, based on fuel cell and radiators physical models, and representing an optimum compromise between weight and drag. The work reveals linear correlation between the TMS parameters and fuel cell power. Significant dependence on fuel cell temperature has also been shown, therefore, three temperature levels were tested. It has also been observed that optimum solutions tend to require too large radiators, difficult to install, so, a limitation was inserted in the optimization cycle and models for three different area limits were generated. Then, regression equations have been determined to correlate the TMS parameters with fuel cell power, for various combinations of fuel cell operating temperature and radiator area limits, accomplishing the purpose of the work. It is recommended, for future works, the conduction of studies to investigate more efficient radiators, heat enhancement devices and TMS large radiators installation solutions.
publishDate 2024
dc.date.none.fl_str_mv 2024-08-09
dc.type.status.fl_str_mv info:eu-repo/semantics/publishedVersion
dc.type.driver.fl_str_mv info:eu-repo/semantics/masterThesis
format masterThesis
status_str publishedVersion
dc.identifier.uri.fl_str_mv https://www.teses.usp.br/teses/disponiveis/18/18161/tde-09092024-155909/
url https://www.teses.usp.br/teses/disponiveis/18/18161/tde-09092024-155909/
dc.language.iso.fl_str_mv eng
language eng
dc.relation.none.fl_str_mv
dc.rights.driver.fl_str_mv Liberar o conteúdo para acesso público.
info:eu-repo/semantics/openAccess
rights_invalid_str_mv Liberar o conteúdo para acesso público.
eu_rights_str_mv openAccess
dc.format.none.fl_str_mv application/pdf
dc.coverage.none.fl_str_mv
dc.publisher.none.fl_str_mv Biblioteca Digitais de Teses e Dissertações da USP
publisher.none.fl_str_mv Biblioteca Digitais de Teses e Dissertações da USP
dc.source.none.fl_str_mv
reponame:Biblioteca Digital de Teses e Dissertações da USP
instname:Universidade de São Paulo (USP)
instacron:USP
instname_str Universidade de São Paulo (USP)
instacron_str USP
institution USP
reponame_str Biblioteca Digital de Teses e Dissertações da USP
collection Biblioteca Digital de Teses e Dissertações da USP
repository.name.fl_str_mv Biblioteca Digital de Teses e Dissertações da USP - Universidade de São Paulo (USP)
repository.mail.fl_str_mv virginia@if.usp.br|| atendimento@aguia.usp.br||virginia@if.usp.br
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