Carbon fibber reinforced polymer use in space launch vehicle propellant tanks - concept and finite element method study
Autor(a) principal: | |
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Data de Publicação: | 2020 |
Outros Autores: | |
Tipo de documento: | Artigo |
Idioma: | eng |
Título da fonte: | Repositório Científico de Acesso Aberto de Portugal (Repositórios Cientìficos) |
Texto Completo: | https://doi.org/10.34624/nmse.v2i4.21072 |
Resumo: | Weight reduction is a never-ending goal in aerospace engineering, especially for a space launch vehicle (SLV), were every gram of mass has a penalty in the vehicle's performance. Since propellant tanks generally weigh more than half of the dry mass of a SLV, it is particularly advantageous to implement composite materials in their construction. Yet, difficulties with oxygen compatibility, permeability and manufacturing maturity dictate that aluminium alloys with high lithium content are still the state of the art in this field. Recent developments in the aerospace composites industry are starting to change this perception, especially regarding Carbon Fibber Reinforced Polymer (CFRP) application. Hence this study, which aims to propose an integral CFRP propellant tank concept and determine mass savings by comparing it to a metallic baseline, through finite element method (FEM) analysis with simulated flight loads. Tank dimensions, geometry and loads were chosen for micro-satellite SLV application. Also, Altair's Optistruct solver was used for FEM calculations, with Altair's HyperWorks for pre and post-processing. A mass reduction of close to 35% has been obtained with comparison to the metallic baseline design for the same boundary conditions. Therefore, a sound and competitive design for a micro-satellite SLV propellant tank has been successfully achieved. |
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Carbon fibber reinforced polymer use in space launch vehicle propellant tanks - concept and finite element method studyWeight reduction is a never-ending goal in aerospace engineering, especially for a space launch vehicle (SLV), were every gram of mass has a penalty in the vehicle's performance. Since propellant tanks generally weigh more than half of the dry mass of a SLV, it is particularly advantageous to implement composite materials in their construction. Yet, difficulties with oxygen compatibility, permeability and manufacturing maturity dictate that aluminium alloys with high lithium content are still the state of the art in this field. Recent developments in the aerospace composites industry are starting to change this perception, especially regarding Carbon Fibber Reinforced Polymer (CFRP) application. Hence this study, which aims to propose an integral CFRP propellant tank concept and determine mass savings by comparing it to a metallic baseline, through finite element method (FEM) analysis with simulated flight loads. Tank dimensions, geometry and loads were chosen for micro-satellite SLV application. Also, Altair's Optistruct solver was used for FEM calculations, with Altair's HyperWorks for pre and post-processing. A mass reduction of close to 35% has been obtained with comparison to the metallic baseline design for the same boundary conditions. Therefore, a sound and competitive design for a micro-satellite SLV propellant tank has been successfully achieved.UA Editora2020-12-11T00:00:00Zinfo:eu-repo/semantics/publishedVersioninfo:eu-repo/semantics/articleapplication/pdfhttps://doi.org/10.34624/nmse.v2i4.21072oai:proa.ua.pt:article/21072Nanomaterials Science & Engineering; Vol 2 No 4 (2020): Nanomaterials Science & Engineering; 175-182Journal of Nanomaterials Science and Nanotechnology; Vol. 2 Núm. 4 (2020): Nanomaterials Science & Engineering; 175-182Journal of Nanomaterials Science and Nanotechnology; Vol. 2 No 4 (2020): Nanomaterials Science & Engineering; 175-182Nanomaterials Science & Engineering; vol. 2 n.º 4 (2020): Nanomaterials Science & Engineering; 175-1822184-70022184-7002reponame:Repositório Científico de Acesso Aberto de Portugal (Repositórios Cientìficos)instname:Agência para a Sociedade do Conhecimento (UMIC) - FCT - Sociedade da Informaçãoinstacron:RCAAPenghttps://proa.ua.pt/index.php/nmse/article/view/21072https://doi.org/10.34624/nmse.v2i4.21072https://proa.ua.pt/index.php/nmse/article/view/21072/16900Copyright (c) 2020 Nanomaterials Science & Engineeringhttp://creativecommons.org/licenses/by-nc/4.0info:eu-repo/semantics/openAccessFernandes, MiguelBrojo, Francisco2022-09-06T02:15:15Zoai:proa.ua.pt:article/21072Portal AgregadorONGhttps://www.rcaap.pt/oai/openaireopendoar:71602024-03-19T15:47:52.472930Repositório Científico de Acesso Aberto de Portugal (Repositórios Cientìficos) - Agência para a Sociedade do Conhecimento (UMIC) - FCT - Sociedade da Informaçãofalse |
dc.title.none.fl_str_mv |
Carbon fibber reinforced polymer use in space launch vehicle propellant tanks - concept and finite element method study |
title |
Carbon fibber reinforced polymer use in space launch vehicle propellant tanks - concept and finite element method study |
spellingShingle |
Carbon fibber reinforced polymer use in space launch vehicle propellant tanks - concept and finite element method study Fernandes, Miguel |
title_short |
Carbon fibber reinforced polymer use in space launch vehicle propellant tanks - concept and finite element method study |
title_full |
Carbon fibber reinforced polymer use in space launch vehicle propellant tanks - concept and finite element method study |
title_fullStr |
Carbon fibber reinforced polymer use in space launch vehicle propellant tanks - concept and finite element method study |
title_full_unstemmed |
Carbon fibber reinforced polymer use in space launch vehicle propellant tanks - concept and finite element method study |
title_sort |
Carbon fibber reinforced polymer use in space launch vehicle propellant tanks - concept and finite element method study |
author |
Fernandes, Miguel |
author_facet |
Fernandes, Miguel Brojo, Francisco |
author_role |
author |
author2 |
Brojo, Francisco |
author2_role |
author |
dc.contributor.author.fl_str_mv |
Fernandes, Miguel Brojo, Francisco |
description |
Weight reduction is a never-ending goal in aerospace engineering, especially for a space launch vehicle (SLV), were every gram of mass has a penalty in the vehicle's performance. Since propellant tanks generally weigh more than half of the dry mass of a SLV, it is particularly advantageous to implement composite materials in their construction. Yet, difficulties with oxygen compatibility, permeability and manufacturing maturity dictate that aluminium alloys with high lithium content are still the state of the art in this field. Recent developments in the aerospace composites industry are starting to change this perception, especially regarding Carbon Fibber Reinforced Polymer (CFRP) application. Hence this study, which aims to propose an integral CFRP propellant tank concept and determine mass savings by comparing it to a metallic baseline, through finite element method (FEM) analysis with simulated flight loads. Tank dimensions, geometry and loads were chosen for micro-satellite SLV application. Also, Altair's Optistruct solver was used for FEM calculations, with Altair's HyperWorks for pre and post-processing. A mass reduction of close to 35% has been obtained with comparison to the metallic baseline design for the same boundary conditions. Therefore, a sound and competitive design for a micro-satellite SLV propellant tank has been successfully achieved. |
publishDate |
2020 |
dc.date.none.fl_str_mv |
2020-12-11T00:00:00Z |
dc.type.status.fl_str_mv |
info:eu-repo/semantics/publishedVersion |
dc.type.driver.fl_str_mv |
info:eu-repo/semantics/article |
format |
article |
status_str |
publishedVersion |
dc.identifier.uri.fl_str_mv |
https://doi.org/10.34624/nmse.v2i4.21072 oai:proa.ua.pt:article/21072 |
url |
https://doi.org/10.34624/nmse.v2i4.21072 |
identifier_str_mv |
oai:proa.ua.pt:article/21072 |
dc.language.iso.fl_str_mv |
eng |
language |
eng |
dc.relation.none.fl_str_mv |
https://proa.ua.pt/index.php/nmse/article/view/21072 https://doi.org/10.34624/nmse.v2i4.21072 https://proa.ua.pt/index.php/nmse/article/view/21072/16900 |
dc.rights.driver.fl_str_mv |
Copyright (c) 2020 Nanomaterials Science & Engineering http://creativecommons.org/licenses/by-nc/4.0 info:eu-repo/semantics/openAccess |
rights_invalid_str_mv |
Copyright (c) 2020 Nanomaterials Science & Engineering http://creativecommons.org/licenses/by-nc/4.0 |
eu_rights_str_mv |
openAccess |
dc.format.none.fl_str_mv |
application/pdf |
dc.publisher.none.fl_str_mv |
UA Editora |
publisher.none.fl_str_mv |
UA Editora |
dc.source.none.fl_str_mv |
Nanomaterials Science & Engineering; Vol 2 No 4 (2020): Nanomaterials Science & Engineering; 175-182 Journal of Nanomaterials Science and Nanotechnology; Vol. 2 Núm. 4 (2020): Nanomaterials Science & Engineering; 175-182 Journal of Nanomaterials Science and Nanotechnology; Vol. 2 No 4 (2020): Nanomaterials Science & Engineering; 175-182 Nanomaterials Science & Engineering; vol. 2 n.º 4 (2020): Nanomaterials Science & Engineering; 175-182 2184-7002 2184-7002 reponame:Repositório Científico de Acesso Aberto de Portugal (Repositórios Cientìficos) instname:Agência para a Sociedade do Conhecimento (UMIC) - FCT - Sociedade da Informação instacron:RCAAP |
instname_str |
Agência para a Sociedade do Conhecimento (UMIC) - FCT - Sociedade da Informação |
instacron_str |
RCAAP |
institution |
RCAAP |
reponame_str |
Repositório Científico de Acesso Aberto de Portugal (Repositórios Cientìficos) |
collection |
Repositório Científico de Acesso Aberto de Portugal (Repositórios Cientìficos) |
repository.name.fl_str_mv |
Repositório Científico de Acesso Aberto de Portugal (Repositórios Cientìficos) - Agência para a Sociedade do Conhecimento (UMIC) - FCT - Sociedade da Informação |
repository.mail.fl_str_mv |
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1799130345583411200 |