Theoretical and Experimental Heat Transfer in Solid Propellant Rocket Engine
Autor(a) principal: | |
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Data de Publicação: | 2019 |
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=S2175-91462019000100334 |
Resumo: | ABSTRACT: Accurate determination of heat flux is an important task not only in the designing aspect, but also in the performance analysis of rocket engines. In this purpose, this work deals with the heat flux determination in a combustion chamber through the inverse method. In this approach, the transient heat flux is determined from the experimental temperature data measured at the outer sidewall of the rocket engine. In this work the physical phenomenon was modeled by the transient one-dimensional heat equation in cylindrical coordinates and the material properties of the chamber were considered constant. Furthermore, the model is solved using the inverse heat conduction problem with least squares modified by the addition of Tikhonov regularization term of zero-order. Moreover, the sensitivity coefficients were obtained by Duhamel’s theorem. Through the regularization parameter, it was able to generate acceptable results even when using data with considerable experimental errors. |
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Journal of Aerospace Technology and Management (Online) |
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Theoretical and Experimental Heat Transfer in Solid Propellant Rocket EngineCombustion chambersHeat fluxHeat conductionIll-posed problemsABSTRACT: Accurate determination of heat flux is an important task not only in the designing aspect, but also in the performance analysis of rocket engines. In this purpose, this work deals with the heat flux determination in a combustion chamber through the inverse method. In this approach, the transient heat flux is determined from the experimental temperature data measured at the outer sidewall of the rocket engine. In this work the physical phenomenon was modeled by the transient one-dimensional heat equation in cylindrical coordinates and the material properties of the chamber were considered constant. Furthermore, the model is solved using the inverse heat conduction problem with least squares modified by the addition of Tikhonov regularization term of zero-order. Moreover, the sensitivity coefficients were obtained by Duhamel’s theorem. Through the regularization parameter, it was able to generate acceptable results even when using data with considerable experimental errors.Departamento de Ciência e Tecnologia Aeroespacial2019-01-01info:eu-repo/semantics/articleinfo:eu-repo/semantics/publishedVersiontext/htmlhttp://old.scielo.br/scielo.php?script=sci_arttext&pid=S2175-91462019000100334Journal of Aerospace Technology and Management v.11 2019reponame:Journal of Aerospace Technology and Management (Online)instname:Departamento de Ciência e Tecnologia Aeroespacial (DCTA)instacron:DCTA10.5028/jatm.v11.1066info:eu-repo/semantics/openAccessVicentin,Izabel Cecilia Ferreira de SouzaMarchi,Carlos HenriqueFoltran,Antonio CarlosMoro,DiegoSilva,Nicholas Dicati Pereira daCampos,Marcos CarvalhoAraki,Luciano KiyoshiDiógenes,Alysson Nuneseng2019-08-21T00:00:00Zoai:scielo:S2175-91462019000100334Revistahttp://www.jatm.com.br/ONGhttps://old.scielo.br/oai/scielo-oai.php||secretary@jatm.com.br2175-91461984-9648opendoar:2019-08-21T00:00Journal of Aerospace Technology and Management (Online) - Departamento de Ciência e Tecnologia Aeroespacial (DCTA)false |
dc.title.none.fl_str_mv |
Theoretical and Experimental Heat Transfer in Solid Propellant Rocket Engine |
title |
Theoretical and Experimental Heat Transfer in Solid Propellant Rocket Engine |
spellingShingle |
Theoretical and Experimental Heat Transfer in Solid Propellant Rocket Engine Vicentin,Izabel Cecilia Ferreira de Souza Combustion chambers Heat flux Heat conduction Ill-posed problems |
title_short |
Theoretical and Experimental Heat Transfer in Solid Propellant Rocket Engine |
title_full |
Theoretical and Experimental Heat Transfer in Solid Propellant Rocket Engine |
title_fullStr |
Theoretical and Experimental Heat Transfer in Solid Propellant Rocket Engine |
title_full_unstemmed |
Theoretical and Experimental Heat Transfer in Solid Propellant Rocket Engine |
title_sort |
Theoretical and Experimental Heat Transfer in Solid Propellant Rocket Engine |
author |
Vicentin,Izabel Cecilia Ferreira de Souza |
author_facet |
Vicentin,Izabel Cecilia Ferreira de Souza Marchi,Carlos Henrique Foltran,Antonio Carlos Moro,Diego Silva,Nicholas Dicati Pereira da Campos,Marcos Carvalho Araki,Luciano Kiyoshi Diógenes,Alysson Nunes |
author_role |
author |
author2 |
Marchi,Carlos Henrique Foltran,Antonio Carlos Moro,Diego Silva,Nicholas Dicati Pereira da Campos,Marcos Carvalho Araki,Luciano Kiyoshi Diógenes,Alysson Nunes |
author2_role |
author author author author author author author |
dc.contributor.author.fl_str_mv |
Vicentin,Izabel Cecilia Ferreira de Souza Marchi,Carlos Henrique Foltran,Antonio Carlos Moro,Diego Silva,Nicholas Dicati Pereira da Campos,Marcos Carvalho Araki,Luciano Kiyoshi Diógenes,Alysson Nunes |
dc.subject.por.fl_str_mv |
Combustion chambers Heat flux Heat conduction Ill-posed problems |
topic |
Combustion chambers Heat flux Heat conduction Ill-posed problems |
description |
ABSTRACT: Accurate determination of heat flux is an important task not only in the designing aspect, but also in the performance analysis of rocket engines. In this purpose, this work deals with the heat flux determination in a combustion chamber through the inverse method. In this approach, the transient heat flux is determined from the experimental temperature data measured at the outer sidewall of the rocket engine. In this work the physical phenomenon was modeled by the transient one-dimensional heat equation in cylindrical coordinates and the material properties of the chamber were considered constant. Furthermore, the model is solved using the inverse heat conduction problem with least squares modified by the addition of Tikhonov regularization term of zero-order. Moreover, the sensitivity coefficients were obtained by Duhamel’s theorem. Through the regularization parameter, it was able to generate acceptable results even when using data with considerable experimental errors. |
publishDate |
2019 |
dc.date.none.fl_str_mv |
2019-01-01 |
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=S2175-91462019000100334 |
url |
http://old.scielo.br/scielo.php?script=sci_arttext&pid=S2175-91462019000100334 |
dc.language.iso.fl_str_mv |
eng |
language |
eng |
dc.relation.none.fl_str_mv |
10.5028/jatm.v11.1066 |
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.11 2019 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 |
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1754732532060913664 |