Studies on Heat Flux Imparted on Thermal Insulation Inside Rocket Motor Containing Double Base Propellant

Detalhes bibliográficos
Autor(a) principal: Kalal,Rakesh Kumar
Data de Publicação: 2019
Outros Autores: Ropia,Balesh, Shekhar,Himanshu, Alegaonkar,Prashant Sudhir
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=S2175-91462019000100327
Resumo: ABSTRACT Thermal insulation inside the rocket motor experience severe pressure and temperature conditions. Experimental determination of heat flux imparted to thermal insulator inside the rocket motor during the static firing is a challenging task. This paper reports experimental determination of heat flux for double base propellant (DBP) in small rocket motor. It includes development of experimental rocket motor, adaptation of water-cooled heat flux sensor on rocket motor, required instrumentation for heat flux time recording and analysis of data. Data are recorded in real time for double base propellant combustion up to the pressure level ~3.6 MPa. Average heat flux imparted to the rocket motor casing is found in the range of 230-300 × 104 W/m2. Heat flux inside the rocket motor varies nearly linear with pressure. A correlation between the heat flux and pressure is also established for measured pressure range.
id DCTA-1_696eb0f773c37e56bb0844bed182da93
oai_identifier_str oai:scielo:S2175-91462019000100327
network_acronym_str DCTA-1
network_name_str Journal of Aerospace Technology and Management (Online)
repository_id_str
spelling Studies on Heat Flux Imparted on Thermal Insulation Inside Rocket Motor Containing Double Base PropellantHeat fluxRocket motorThermal insulationDouble base propellantABSTRACT Thermal insulation inside the rocket motor experience severe pressure and temperature conditions. Experimental determination of heat flux imparted to thermal insulator inside the rocket motor during the static firing is a challenging task. This paper reports experimental determination of heat flux for double base propellant (DBP) in small rocket motor. It includes development of experimental rocket motor, adaptation of water-cooled heat flux sensor on rocket motor, required instrumentation for heat flux time recording and analysis of data. Data are recorded in real time for double base propellant combustion up to the pressure level ~3.6 MPa. Average heat flux imparted to the rocket motor casing is found in the range of 230-300 × 104 W/m2. Heat flux inside the rocket motor varies nearly linear with pressure. A correlation between the heat flux and pressure is also established for measured pressure range.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=S2175-91462019000100327Journal 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.v11.1058info:eu-repo/semantics/openAccessKalal,Rakesh KumarRopia,BaleshShekhar,HimanshuAlegaonkar,Prashant Sudhireng2019-07-03T00:00:00Zoai:scielo:S2175-91462019000100327Revistahttp://www.jatm.com.br/ONGhttps://old.scielo.br/oai/scielo-oai.php||secretary@jatm.com.br2175-91461984-9648opendoar:2019-07-03T00:00Journal of Aerospace Technology and Management (Online) - Departamento de Ciência e Tecnologia Aeroespacial (DCTA)false
dc.title.none.fl_str_mv Studies on Heat Flux Imparted on Thermal Insulation Inside Rocket Motor Containing Double Base Propellant
title Studies on Heat Flux Imparted on Thermal Insulation Inside Rocket Motor Containing Double Base Propellant
spellingShingle Studies on Heat Flux Imparted on Thermal Insulation Inside Rocket Motor Containing Double Base Propellant
Kalal,Rakesh Kumar
Heat flux
Rocket motor
Thermal insulation
Double base propellant
title_short Studies on Heat Flux Imparted on Thermal Insulation Inside Rocket Motor Containing Double Base Propellant
title_full Studies on Heat Flux Imparted on Thermal Insulation Inside Rocket Motor Containing Double Base Propellant
title_fullStr Studies on Heat Flux Imparted on Thermal Insulation Inside Rocket Motor Containing Double Base Propellant
title_full_unstemmed Studies on Heat Flux Imparted on Thermal Insulation Inside Rocket Motor Containing Double Base Propellant
title_sort Studies on Heat Flux Imparted on Thermal Insulation Inside Rocket Motor Containing Double Base Propellant
author Kalal,Rakesh Kumar
author_facet Kalal,Rakesh Kumar
Ropia,Balesh
Shekhar,Himanshu
Alegaonkar,Prashant Sudhir
author_role author
author2 Ropia,Balesh
Shekhar,Himanshu
Alegaonkar,Prashant Sudhir
author2_role author
author
author
dc.contributor.author.fl_str_mv Kalal,Rakesh Kumar
Ropia,Balesh
Shekhar,Himanshu
Alegaonkar,Prashant Sudhir
dc.subject.por.fl_str_mv Heat flux
Rocket motor
Thermal insulation
Double base propellant
topic Heat flux
Rocket motor
Thermal insulation
Double base propellant
description ABSTRACT Thermal insulation inside the rocket motor experience severe pressure and temperature conditions. Experimental determination of heat flux imparted to thermal insulator inside the rocket motor during the static firing is a challenging task. This paper reports experimental determination of heat flux for double base propellant (DBP) in small rocket motor. It includes development of experimental rocket motor, adaptation of water-cooled heat flux sensor on rocket motor, required instrumentation for heat flux time recording and analysis of data. Data are recorded in real time for double base propellant combustion up to the pressure level ~3.6 MPa. Average heat flux imparted to the rocket motor casing is found in the range of 230-300 × 104 W/m2. Heat flux inside the rocket motor varies nearly linear with pressure. A correlation between the heat flux and pressure is also established for measured pressure range.
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=S2175-91462019000100327
url http://old.scielo.br/scielo.php?script=sci_arttext&pid=S2175-91462019000100327
dc.language.iso.fl_str_mv eng
language eng
dc.relation.none.fl_str_mv 10.5028/jatm.v11.1058
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
_version_ 1754732532049379328

Registros relacionados