Kick Solid Rocket Motor Multidisciplinary Design Optimization Using Genetic Algorithm
Autor(a) principal: | |
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Data de Publicação: | 2013 |
Outros Autores: | , |
Tipo de documento: | Artigo |
Idioma: | eng |
Título da fonte: | Journal of Aerospace Technology and Management (Online) |
Texto Completo: | http://old.scielo.br/scielo.php?script=sci_arttext&pid=S2175-91462013000300293 |
Resumo: | ABSTRACT: In this paper, a multidisciplinary design optimization (MDO) approach of a solid propellant kick rocket motor is considered. A genetic algorithm optimization method has been used. The optimized kick solid rocket motor (KSRM) is capable of delivering a small satellite of 200 kg to a circular low earth orbit (LEO) of 600 km altitude. The KSRM should accelerate from the initial apogee velocity of 5000 m/s up to the orbital insertion velocity of 7560 m/s. The KSRM design variables and the orbital insertion trajectory profile variables were optimized simultaneously, whereas the mass characteristics of the payload deployment module were assigned. A depleted shutdown condition was considered, to avoid the necessity of a thrust termination device, resulting in a reduced total mass of the KSRM. The results show that the proposed optimization approach was able to find the convergence of the optimal solution with highly acceptable value for conceptual design phase. |
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Journal of Aerospace Technology and Management (Online) |
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Kick Solid Rocket Motor Multidisciplinary Design Optimization Using Genetic AlgorithmKick solid rocket motorMultidisciplinary design optimizationGenetic algorithmABSTRACT: In this paper, a multidisciplinary design optimization (MDO) approach of a solid propellant kick rocket motor is considered. A genetic algorithm optimization method has been used. The optimized kick solid rocket motor (KSRM) is capable of delivering a small satellite of 200 kg to a circular low earth orbit (LEO) of 600 km altitude. The KSRM should accelerate from the initial apogee velocity of 5000 m/s up to the orbital insertion velocity of 7560 m/s. The KSRM design variables and the orbital insertion trajectory profile variables were optimized simultaneously, whereas the mass characteristics of the payload deployment module were assigned. A depleted shutdown condition was considered, to avoid the necessity of a thrust termination device, resulting in a reduced total mass of the KSRM. The results show that the proposed optimization approach was able to find the convergence of the optimal solution with highly acceptable value for conceptual design phase.Departamento de Ciência e Tecnologia Aeroespacial2013-09-01info:eu-repo/semantics/articleinfo:eu-repo/semantics/publishedVersiontext/htmlhttp://old.scielo.br/scielo.php?script=sci_arttext&pid=S2175-91462013000300293Journal of Aerospace Technology and Management v.5 n.3 2013reponame:Journal of Aerospace Technology and Management (Online)instname:Departamento de Ciência e Tecnologia Aeroespacial (DCTA)instacron:DCTA10.5028/jatm.v5i3.225info:eu-repo/semantics/openAccessVillanueva,Fredy MarcellLinshu,HeDajun,Xueng2017-05-24T00:00:00Zoai:scielo:S2175-91462013000300293Revistahttp://www.jatm.com.br/ONGhttps://old.scielo.br/oai/scielo-oai.php||secretary@jatm.com.br2175-91461984-9648opendoar:2017-05-24T00:00Journal of Aerospace Technology and Management (Online) - Departamento de Ciência e Tecnologia Aeroespacial (DCTA)false |
dc.title.none.fl_str_mv |
Kick Solid Rocket Motor Multidisciplinary Design Optimization Using Genetic Algorithm |
title |
Kick Solid Rocket Motor Multidisciplinary Design Optimization Using Genetic Algorithm |
spellingShingle |
Kick Solid Rocket Motor Multidisciplinary Design Optimization Using Genetic Algorithm Villanueva,Fredy Marcell Kick solid rocket motor Multidisciplinary design optimization Genetic algorithm |
title_short |
Kick Solid Rocket Motor Multidisciplinary Design Optimization Using Genetic Algorithm |
title_full |
Kick Solid Rocket Motor Multidisciplinary Design Optimization Using Genetic Algorithm |
title_fullStr |
Kick Solid Rocket Motor Multidisciplinary Design Optimization Using Genetic Algorithm |
title_full_unstemmed |
Kick Solid Rocket Motor Multidisciplinary Design Optimization Using Genetic Algorithm |
title_sort |
Kick Solid Rocket Motor Multidisciplinary Design Optimization Using Genetic Algorithm |
author |
Villanueva,Fredy Marcell |
author_facet |
Villanueva,Fredy Marcell Linshu,He Dajun,Xu |
author_role |
author |
author2 |
Linshu,He Dajun,Xu |
author2_role |
author author |
dc.contributor.author.fl_str_mv |
Villanueva,Fredy Marcell Linshu,He Dajun,Xu |
dc.subject.por.fl_str_mv |
Kick solid rocket motor Multidisciplinary design optimization Genetic algorithm |
topic |
Kick solid rocket motor Multidisciplinary design optimization Genetic algorithm |
description |
ABSTRACT: In this paper, a multidisciplinary design optimization (MDO) approach of a solid propellant kick rocket motor is considered. A genetic algorithm optimization method has been used. The optimized kick solid rocket motor (KSRM) is capable of delivering a small satellite of 200 kg to a circular low earth orbit (LEO) of 600 km altitude. The KSRM should accelerate from the initial apogee velocity of 5000 m/s up to the orbital insertion velocity of 7560 m/s. The KSRM design variables and the orbital insertion trajectory profile variables were optimized simultaneously, whereas the mass characteristics of the payload deployment module were assigned. A depleted shutdown condition was considered, to avoid the necessity of a thrust termination device, resulting in a reduced total mass of the KSRM. The results show that the proposed optimization approach was able to find the convergence of the optimal solution with highly acceptable value for conceptual design phase. |
publishDate |
2013 |
dc.date.none.fl_str_mv |
2013-09-01 |
dc.type.driver.fl_str_mv |
info:eu-repo/semantics/article |
dc.type.status.fl_str_mv |
info:eu-repo/semantics/publishedVersion |
format |
article |
status_str |
publishedVersion |
dc.identifier.uri.fl_str_mv |
http://old.scielo.br/scielo.php?script=sci_arttext&pid=S2175-91462013000300293 |
url |
http://old.scielo.br/scielo.php?script=sci_arttext&pid=S2175-91462013000300293 |
dc.language.iso.fl_str_mv |
eng |
language |
eng |
dc.relation.none.fl_str_mv |
10.5028/jatm.v5i3.225 |
dc.rights.driver.fl_str_mv |
info:eu-repo/semantics/openAccess |
eu_rights_str_mv |
openAccess |
dc.format.none.fl_str_mv |
text/html |
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 |
Journal of Aerospace Technology and Management v.5 n.3 2013 reponame:Journal of Aerospace Technology and Management (Online) instname:Departamento de Ciência e Tecnologia Aeroespacial (DCTA) instacron:DCTA |
instname_str |
Departamento de Ciência e Tecnologia Aeroespacial (DCTA) |
instacron_str |
DCTA |
institution |
DCTA |
reponame_str |
Journal of Aerospace Technology and Management (Online) |
collection |
Journal of Aerospace Technology and Management (Online) |
repository.name.fl_str_mv |
Journal of Aerospace Technology and Management (Online) - Departamento de Ciência e Tecnologia Aeroespacial (DCTA) |
repository.mail.fl_str_mv |
||secretary@jatm.com.br |
_version_ |
1754732530824642560 |