Theoretical and Experimental Heat Transfer in Solid Propellant Rocket Engine

Detalhes bibliográficos
Autor(a) principal: Vicentin,Izabel Cecilia Ferreira de Souza
Data de Publicação: 2019
Outros Autores: Marchi,Carlos Henrique, Foltran,Antonio Carlos, Moro,Diego, Silva,Nicholas Dicati Pereira da, Campos,Marcos Carvalho, Araki,Luciano Kiyoshi, Diógenes,Alysson Nunes
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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spelling 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
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dc.identifier.uri.fl_str_mv http://old.scielo.br/scielo.php?script=sci_arttext&pid=S2175-91462019000100334
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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)
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