Swirl Injection Effects on Hybrid Rocket Motors
Autor(a) principal: | |
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Data de Publicação: | 2015 |
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=S2175-91462015000400418 |
Resumo: | ABSTRACT: In the last decades, hybrid rocket engines have been increasingly studied and used in space vehicles. However, the low regression rates and specific impulses still represent major drawbacks to this technology. The objective of this study was to quantify the relative improvement of regression rate values with the use of a swirling flow injector in comparison to an axial injector. Seven tests were conducted with axial injection and seven with swirl injection. Regression rate results were compared, and it was found that swirl injection improved regression rates in 50% for mass fluxes higher than 45 kg·s-1·m-2. It was possible to see radiation, kinetic and diffusion theory on the logarithmic plot of regression rate per oxidizer flux yielded by both injectors. A strong agreement with experimental findings of regression rates in the literature parameters is reported. |
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Journal of Aerospace Technology and Management (Online) |
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Swirl Injection Effects on Hybrid Rocket MotorsHybrid rocket motorSwirl injectorSolid fuel regression ratesABSTRACT: In the last decades, hybrid rocket engines have been increasingly studied and used in space vehicles. However, the low regression rates and specific impulses still represent major drawbacks to this technology. The objective of this study was to quantify the relative improvement of regression rate values with the use of a swirling flow injector in comparison to an axial injector. Seven tests were conducted with axial injection and seven with swirl injection. Regression rate results were compared, and it was found that swirl injection improved regression rates in 50% for mass fluxes higher than 45 kg·s-1·m-2. It was possible to see radiation, kinetic and diffusion theory on the logarithmic plot of regression rate per oxidizer flux yielded by both injectors. A strong agreement with experimental findings of regression rates in the literature parameters is reported.Departamento de Ciência e Tecnologia Aeroespacial2015-12-01info:eu-repo/semantics/articleinfo:eu-repo/semantics/publishedVersiontext/htmlhttp://old.scielo.br/scielo.php?script=sci_arttext&pid=S2175-91462015000400418Journal of Aerospace Technology and Management v.7 n.4 2015reponame:Journal of Aerospace Technology and Management (Online)instname:Departamento de Ciência e Tecnologia Aeroespacial (DCTA)instacron:DCTA10.5028/jatm.v7i4.368info:eu-repo/semantics/openAccessGomes,Susane RibeiroRocco,LeopoldoRocco,José Atílio Fritz F.eng2017-05-23T00:00:00Zoai:scielo:S2175-91462015000400418Revistahttp://www.jatm.com.br/ONGhttps://old.scielo.br/oai/scielo-oai.php||secretary@jatm.com.br2175-91461984-9648opendoar:2017-05-23T00:00Journal of Aerospace Technology and Management (Online) - Departamento de Ciência e Tecnologia Aeroespacial (DCTA)false |
dc.title.none.fl_str_mv |
Swirl Injection Effects on Hybrid Rocket Motors |
title |
Swirl Injection Effects on Hybrid Rocket Motors |
spellingShingle |
Swirl Injection Effects on Hybrid Rocket Motors Gomes,Susane Ribeiro Hybrid rocket motor Swirl injector Solid fuel regression rates |
title_short |
Swirl Injection Effects on Hybrid Rocket Motors |
title_full |
Swirl Injection Effects on Hybrid Rocket Motors |
title_fullStr |
Swirl Injection Effects on Hybrid Rocket Motors |
title_full_unstemmed |
Swirl Injection Effects on Hybrid Rocket Motors |
title_sort |
Swirl Injection Effects on Hybrid Rocket Motors |
author |
Gomes,Susane Ribeiro |
author_facet |
Gomes,Susane Ribeiro Rocco,Leopoldo Rocco,José Atílio Fritz F. |
author_role |
author |
author2 |
Rocco,Leopoldo Rocco,José Atílio Fritz F. |
author2_role |
author author |
dc.contributor.author.fl_str_mv |
Gomes,Susane Ribeiro Rocco,Leopoldo Rocco,José Atílio Fritz F. |
dc.subject.por.fl_str_mv |
Hybrid rocket motor Swirl injector Solid fuel regression rates |
topic |
Hybrid rocket motor Swirl injector Solid fuel regression rates |
description |
ABSTRACT: In the last decades, hybrid rocket engines have been increasingly studied and used in space vehicles. However, the low regression rates and specific impulses still represent major drawbacks to this technology. The objective of this study was to quantify the relative improvement of regression rate values with the use of a swirling flow injector in comparison to an axial injector. Seven tests were conducted with axial injection and seven with swirl injection. Regression rate results were compared, and it was found that swirl injection improved regression rates in 50% for mass fluxes higher than 45 kg·s-1·m-2. It was possible to see radiation, kinetic and diffusion theory on the logarithmic plot of regression rate per oxidizer flux yielded by both injectors. A strong agreement with experimental findings of regression rates in the literature parameters is reported. |
publishDate |
2015 |
dc.date.none.fl_str_mv |
2015-12-01 |
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=S2175-91462015000400418 |
url |
http://old.scielo.br/scielo.php?script=sci_arttext&pid=S2175-91462015000400418 |
dc.language.iso.fl_str_mv |
eng |
language |
eng |
dc.relation.none.fl_str_mv |
10.5028/jatm.v7i4.368 |
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.7 n.4 2015 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_ |
1754732531261898752 |