Anomalous Behavior of a Solid Rocket Motor Nozzle Insert During Static Firing Test
Autor(a) principal: | |
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Data de Publicação: | 2016 |
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=S2175-91462016000400483 |
Resumo: | ABSTRACT This paper presents the study and development of a firing test used to evaluate the behavior of a solid rocket motor. The motivation for the development of a subscale solid rocket motor with end burning propellant grain geometry arose from the need to evaluate the nozzle inserts of graphite for the possible replacement with the carbon fiber-reinforced carbon composite. These subscale solid rocket motors, simulating full scale motor operating time, but with mass flow far below, aim to determine the ablative characteristics of composite materials as a function of operating time. The objective was to correlate the mass flow between subscale solid rocket motors and full scale using insert data materials such as graphite and carbon fiber-reinforced carbon composites, which have ablative characteristics determined in subscale solid rocket motors used at the Instituto de Aeronáutica e Espaço. The critical section to evaluate the test device is rocket nozzle throat region. Analysis of the materials of the subsonic and supersonic nozzle insert parts was performed after the burning tests. It was found the formation of a thin layer of material deposited after the test. The deposited coating layer was analyzed by electron dispersive x-ray analysis and scanning electron microscopy. The results analyzed by these methods showed that there were aluminum and carbon in the coating. Finally, the material was analyzed by x-ray diffraction, and the results showed the presence of aluminum oxide. It was also noticed that, because of the unexpected coating deposition forming material in exit conical and throat of the insert that the effect of ablation was not observed. |
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Anomalous Behavior of a Solid Rocket Motor Nozzle Insert During Static Firing TestPropulsionSubscale motorNozzle insertsGraphiteFiring testABSTRACT This paper presents the study and development of a firing test used to evaluate the behavior of a solid rocket motor. The motivation for the development of a subscale solid rocket motor with end burning propellant grain geometry arose from the need to evaluate the nozzle inserts of graphite for the possible replacement with the carbon fiber-reinforced carbon composite. These subscale solid rocket motors, simulating full scale motor operating time, but with mass flow far below, aim to determine the ablative characteristics of composite materials as a function of operating time. The objective was to correlate the mass flow between subscale solid rocket motors and full scale using insert data materials such as graphite and carbon fiber-reinforced carbon composites, which have ablative characteristics determined in subscale solid rocket motors used at the Instituto de Aeronáutica e Espaço. The critical section to evaluate the test device is rocket nozzle throat region. Analysis of the materials of the subsonic and supersonic nozzle insert parts was performed after the burning tests. It was found the formation of a thin layer of material deposited after the test. The deposited coating layer was analyzed by electron dispersive x-ray analysis and scanning electron microscopy. The results analyzed by these methods showed that there were aluminum and carbon in the coating. Finally, the material was analyzed by x-ray diffraction, and the results showed the presence of aluminum oxide. It was also noticed that, because of the unexpected coating deposition forming material in exit conical and throat of the insert that the effect of ablation was not observed.Departamento de Ciência e Tecnologia Aeroespacial2016-12-01info:eu-repo/semantics/articleinfo:eu-repo/semantics/publishedVersiontext/htmlhttp://old.scielo.br/scielo.php?script=sci_arttext&pid=S2175-91462016000400483Journal of Aerospace Technology and Management v.8 n.4 2016reponame:Journal of Aerospace Technology and Management (Online)instname:Departamento de Ciência e Tecnologia Aeroespacial (DCTA)instacron:DCTA10.5028/jatm.v8i4.663info:eu-repo/semantics/openAccessReis,Ronald IzidoroShimote,Wilson KiyoshiPardini,Luiz Claudioeng2016-11-25T00:00:00Zoai:scielo:S2175-91462016000400483Revistahttp://www.jatm.com.br/ONGhttps://old.scielo.br/oai/scielo-oai.php||secretary@jatm.com.br2175-91461984-9648opendoar:2016-11-25T00:00Journal of Aerospace Technology and Management (Online) - Departamento de Ciência e Tecnologia Aeroespacial (DCTA)false |
dc.title.none.fl_str_mv |
Anomalous Behavior of a Solid Rocket Motor Nozzle Insert During Static Firing Test |
title |
Anomalous Behavior of a Solid Rocket Motor Nozzle Insert During Static Firing Test |
spellingShingle |
Anomalous Behavior of a Solid Rocket Motor Nozzle Insert During Static Firing Test Reis,Ronald Izidoro Propulsion Subscale motor Nozzle inserts Graphite Firing test |
title_short |
Anomalous Behavior of a Solid Rocket Motor Nozzle Insert During Static Firing Test |
title_full |
Anomalous Behavior of a Solid Rocket Motor Nozzle Insert During Static Firing Test |
title_fullStr |
Anomalous Behavior of a Solid Rocket Motor Nozzle Insert During Static Firing Test |
title_full_unstemmed |
Anomalous Behavior of a Solid Rocket Motor Nozzle Insert During Static Firing Test |
title_sort |
Anomalous Behavior of a Solid Rocket Motor Nozzle Insert During Static Firing Test |
author |
Reis,Ronald Izidoro |
author_facet |
Reis,Ronald Izidoro Shimote,Wilson Kiyoshi Pardini,Luiz Claudio |
author_role |
author |
author2 |
Shimote,Wilson Kiyoshi Pardini,Luiz Claudio |
author2_role |
author author |
dc.contributor.author.fl_str_mv |
Reis,Ronald Izidoro Shimote,Wilson Kiyoshi Pardini,Luiz Claudio |
dc.subject.por.fl_str_mv |
Propulsion Subscale motor Nozzle inserts Graphite Firing test |
topic |
Propulsion Subscale motor Nozzle inserts Graphite Firing test |
description |
ABSTRACT This paper presents the study and development of a firing test used to evaluate the behavior of a solid rocket motor. The motivation for the development of a subscale solid rocket motor with end burning propellant grain geometry arose from the need to evaluate the nozzle inserts of graphite for the possible replacement with the carbon fiber-reinforced carbon composite. These subscale solid rocket motors, simulating full scale motor operating time, but with mass flow far below, aim to determine the ablative characteristics of composite materials as a function of operating time. The objective was to correlate the mass flow between subscale solid rocket motors and full scale using insert data materials such as graphite and carbon fiber-reinforced carbon composites, which have ablative characteristics determined in subscale solid rocket motors used at the Instituto de Aeronáutica e Espaço. The critical section to evaluate the test device is rocket nozzle throat region. Analysis of the materials of the subsonic and supersonic nozzle insert parts was performed after the burning tests. It was found the formation of a thin layer of material deposited after the test. The deposited coating layer was analyzed by electron dispersive x-ray analysis and scanning electron microscopy. The results analyzed by these methods showed that there were aluminum and carbon in the coating. Finally, the material was analyzed by x-ray diffraction, and the results showed the presence of aluminum oxide. It was also noticed that, because of the unexpected coating deposition forming material in exit conical and throat of the insert that the effect of ablation was not observed. |
publishDate |
2016 |
dc.date.none.fl_str_mv |
2016-12-01 |
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=S2175-91462016000400483 |
url |
http://old.scielo.br/scielo.php?script=sci_arttext&pid=S2175-91462016000400483 |
dc.language.iso.fl_str_mv |
eng |
language |
eng |
dc.relation.none.fl_str_mv |
10.5028/jatm.v8i4.663 |
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.8 n.4 2016 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_ |
1754732531583811584 |