An optimized hybrid rocket motor for the SARA platform reentry system

Detalhes bibliográficos
Autor(a) principal: Cás, Pedro Luiz Kaled Da
Data de Publicação: 2012
Outros Autores: Vilanova, Cristiano Queiroz, Barcelos Júnior, Manuel Nascimento Dias, Veras, Carlos Alberto Gurgel
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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spelling 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
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