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dc.contributor.authorCás, Pedro Luiz Kaled Dapt_BR
dc.contributor.authorVilanova, Cristiano Queirozpt_BR
dc.contributor.authorBarcelos Júnior, Manuel Nascimento Diaspt_BR
dc.contributor.authorVeras, Carlos Alberto Gurgelpt_BR
dc.date.accessioned2017-12-07T05:01:40Z-
dc.date.available2017-12-07T05:01:40Z-
dc.date.issued2012-09pt_BR
dc.identifier.citationCAS, 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.pt_BR
dc.identifier.urihttp://repositorio.unb.br/handle/10482/28646-
dc.language.isoenpt_BR
dc.publisherDepartamento de Ciência e Tecnologia Aeroespacialpt_BR
dc.rightsAcesso Abertopt_BR
dc.titleAn optimized hybrid rocket motor for the SARA platform reentry systempt_BR
dc.typeArtigopt_BR
dc.subject.keywordPropulsão de foguetept_BR
dc.subject.keywordSatélitespt_BR
dc.subject.keywordEngenharia aeroespacialpt_BR
dc.rights.licenseJournal 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.-
dc.identifier.doihttps://dx.doi.org/10.5028/jatm.2012.04032312pt_BR
dc.description.abstract1This 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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