An optimized hybrid rocket motor for the SARA platform reentry system
Autor(a) principal: | |
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Data de Publicação: | 2012 |
Outros Autores: | , , |
Tipo de documento: | Artigo |
Idioma: | eng |
Título da fonte: | Repositório Institucional da UnB |
Texto Completo: | http://repositorio.unb.br/handle/10482/28646 https://dx.doi.org/10.5028/jatm.2012.04032312 |
Resumo: | This paper has described a system design process, based on a multidisciplinary optimization technique, of a conceptual optimized hybrid propellant rocket motor. The proposed engine could be a technological option for the reentry maneuvering system of the Brazilian recoverable satellite (SARA), which was designed by the Brazilian Institute of Aeronautics and Space. The resulting optimized propulsion system must be viewed as a proof of concept allowing comparison to more conventional technologies, i.e., liquid and solid motors. Design effort was conducted for hybrid propellants engines based on a liquefying fuel (solid paraffin) and two different oxidizers, H2O2 (90% high-testperoxide) and self-pressurizing N2O. The multidisciplinary configuration optimization technique was supported on geometrical operating parameters of the motor, rather than on performance, in order to facilitate subsequent design and fabrication. Results from the code presented a hybrid motor, which was considered a competitive alternative for the deboost engine when compared to the traditional chemical systems, solid and liquid bipropellant, and monopropellant. The estimated mass of the reentry system, for the cases addressed in this study, varied from 22 to 29 kg, which is lower than either liquid bipropellant or solid engines formerly proposed. |
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An optimized hybrid rocket motor for the SARA platform reentry systemPropulsão de fogueteSatélitesEngenharia aeroespacialThis paper has described a system design process, based on a multidisciplinary optimization technique, of a conceptual optimized hybrid propellant rocket motor. The proposed engine could be a technological option for the reentry maneuvering system of the Brazilian recoverable satellite (SARA), which was designed by the Brazilian Institute of Aeronautics and Space. The resulting optimized propulsion system must be viewed as a proof of concept allowing comparison to more conventional technologies, i.e., liquid and solid motors. Design effort was conducted for hybrid propellants engines based on a liquefying fuel (solid paraffin) and two different oxidizers, H2O2 (90% high-testperoxide) and self-pressurizing N2O. The multidisciplinary configuration optimization technique was supported on geometrical operating parameters of the motor, rather than on performance, in order to facilitate subsequent design and fabrication. Results from the code presented a hybrid motor, which was considered a competitive alternative for the deboost engine when compared to the traditional chemical systems, solid and liquid bipropellant, and monopropellant. The estimated mass of the reentry system, for the cases addressed in this study, varied from 22 to 29 kg, which is lower than either liquid bipropellant or solid engines formerly proposed.Faculdade UnB Gama (FGA)Departamento de Ciência e Tecnologia Aeroespacial2017-12-07T05:01:40Z2017-12-07T05:01:40Z2012-09info:eu-repo/semantics/publishedVersioninfo:eu-repo/semantics/articleapplication/pdfCAS, Pedro Luiz Kaled Da et al. An optimized hybrid rocket motor for the SARA platform reentry system. Journal of Aerospace Technology and Management, São José dos Campos, v. 4, n. 3, p. 317-330, jul./set. 2012. DOI: https://doi.org/10.5028/jatm.2012.04032312. Disponível em: http://www.scielo.br/scielo.php?script=sci_arttext&pid=S2175-91462012000300317&lng=en&nrm=iso. Acesso em: 04 dez. 2020.http://repositorio.unb.br/handle/10482/28646https://dx.doi.org/10.5028/jatm.2012.04032312Journal of Aerospace Technology and Management - This is an Open Access article distributed under the terms of the Creative Commons Attribution License, which permits unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited (CC BY 4.0). Fonte: https://www.scielo.br/scielo.php?script=sci_arttext&pid=S2175-91462012000300317. Acesso em: 04 dez. 2020.info:eu-repo/semantics/openAccessCás, Pedro Luiz Kaled DaVilanova, Cristiano QueirozBarcelos Júnior, Manuel Nascimento DiasVeras, Carlos Alberto Gurgelengreponame:Repositório Institucional da UnBinstname:Universidade de Brasília (UnB)instacron:UNB2023-08-01T18:57:26Zoai:repositorio.unb.br:10482/28646Repositório InstitucionalPUBhttps://repositorio.unb.br/oai/requestrepositorio@unb.bropendoar:2023-08-01T18:57:26Repositório Institucional da UnB - Universidade de Brasília (UnB)false |
dc.title.none.fl_str_mv |
An optimized hybrid rocket motor for the SARA platform reentry system |
title |
An optimized hybrid rocket motor for the SARA platform reentry system |
spellingShingle |
An optimized hybrid rocket motor for the SARA platform reentry system Cás, Pedro Luiz Kaled Da Propulsão de foguete Satélites Engenharia aeroespacial |
title_short |
An optimized hybrid rocket motor for the SARA platform reentry system |
title_full |
An optimized hybrid rocket motor for the SARA platform reentry system |
title_fullStr |
An optimized hybrid rocket motor for the SARA platform reentry system |
title_full_unstemmed |
An optimized hybrid rocket motor for the SARA platform reentry system |
title_sort |
An optimized hybrid rocket motor for the SARA platform reentry system |
author |
Cás, Pedro Luiz Kaled Da |
author_facet |
Cás, Pedro Luiz Kaled Da Vilanova, Cristiano Queiroz Barcelos Júnior, Manuel Nascimento Dias Veras, Carlos Alberto Gurgel |
author_role |
author |
author2 |
Vilanova, Cristiano Queiroz Barcelos Júnior, Manuel Nascimento Dias Veras, Carlos Alberto Gurgel |
author2_role |
author author author |
dc.contributor.author.fl_str_mv |
Cás, Pedro Luiz Kaled Da Vilanova, Cristiano Queiroz Barcelos Júnior, Manuel Nascimento Dias Veras, Carlos Alberto Gurgel |
dc.subject.por.fl_str_mv |
Propulsão de foguete Satélites Engenharia aeroespacial |
topic |
Propulsão de foguete Satélites Engenharia aeroespacial |
description |
This paper has described a system design process, based on a multidisciplinary optimization technique, of a conceptual optimized hybrid propellant rocket motor. The proposed engine could be a technological option for the reentry maneuvering system of the Brazilian recoverable satellite (SARA), which was designed by the Brazilian Institute of Aeronautics and Space. The resulting optimized propulsion system must be viewed as a proof of concept allowing comparison to more conventional technologies, i.e., liquid and solid motors. Design effort was conducted for hybrid propellants engines based on a liquefying fuel (solid paraffin) and two different oxidizers, H2O2 (90% high-testperoxide) and self-pressurizing N2O. The multidisciplinary configuration optimization technique was supported on geometrical operating parameters of the motor, rather than on performance, in order to facilitate subsequent design and fabrication. Results from the code presented a hybrid motor, which was considered a competitive alternative for the deboost engine when compared to the traditional chemical systems, solid and liquid bipropellant, and monopropellant. The estimated mass of the reentry system, for the cases addressed in this study, varied from 22 to 29 kg, which is lower than either liquid bipropellant or solid engines formerly proposed. |
publishDate |
2012 |
dc.date.none.fl_str_mv |
2012-09 2017-12-07T05:01:40Z 2017-12-07T05:01:40Z |
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 |
CAS, Pedro Luiz Kaled Da et al. An optimized hybrid rocket motor for the SARA platform reentry system. Journal of Aerospace Technology and Management, São José dos Campos, v. 4, n. 3, p. 317-330, jul./set. 2012. DOI: https://doi.org/10.5028/jatm.2012.04032312. Disponível em: http://www.scielo.br/scielo.php?script=sci_arttext&pid=S2175-91462012000300317&lng=en&nrm=iso. Acesso em: 04 dez. 2020. http://repositorio.unb.br/handle/10482/28646 https://dx.doi.org/10.5028/jatm.2012.04032312 |
identifier_str_mv |
CAS, Pedro Luiz Kaled Da et al. An optimized hybrid rocket motor for the SARA platform reentry system. Journal of Aerospace Technology and Management, São José dos Campos, v. 4, n. 3, p. 317-330, jul./set. 2012. DOI: https://doi.org/10.5028/jatm.2012.04032312. Disponível em: http://www.scielo.br/scielo.php?script=sci_arttext&pid=S2175-91462012000300317&lng=en&nrm=iso. Acesso em: 04 dez. 2020. |
url |
http://repositorio.unb.br/handle/10482/28646 https://dx.doi.org/10.5028/jatm.2012.04032312 |
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 |
Departamento de Ciência e Tecnologia Aeroespacial |
publisher.none.fl_str_mv |
Departamento de Ciência e Tecnologia Aeroespacial |
dc.source.none.fl_str_mv |
reponame:Repositório Institucional da UnB instname:Universidade de Brasília (UnB) instacron:UNB |
instname_str |
Universidade de Brasília (UnB) |
instacron_str |
UNB |
institution |
UNB |
reponame_str |
Repositório Institucional da UnB |
collection |
Repositório Institucional da UnB |
repository.name.fl_str_mv |
Repositório Institucional da UnB - Universidade de Brasília (UnB) |
repository.mail.fl_str_mv |
repositorio@unb.br |
_version_ |
1814508217461374976 |