Flight path analysis in sounding rocket “Libertador I” with computational simulation on three degrees of freedom

Autores
Murcia, J.; Gomez, S.; Cerón Muñoz, H.; Portilla, G.
Año de publicación
2014
Idioma
inglés
Tipo de recurso
documento de conferencia
Estado
versión publicada
Descripción
This paper presents obtained results from computer simulations in order to analyze the flight path of the sounding rocket Libertador I, developed in 2012 at the Fundación Universitaria Los Libertadores. The main aspects that affect the motion of a rocket are propulsion and aerodynamics effects. Numerical algorithms were implemented to value the thrust provided by the rocket motor as well as aerodynamic loads. Then, the differential equations of the motion are solved using the Runge-Kutta method, RK9. Trajectory and other numerical results are calculated from a code developed in FORTRAN. Finally, graphs of the flight path, curves of the vehicle velocity as function of time are presented. Also, the algorithm permits to determine the maximum altitude and possible impact sites.
Facultad de Ingeniería
Materia
Ingeniería Aeronáutica
Simulación
trayectoria de vuelo
rocket motor
solid propellant
sounding rocket
Nivel de accesibilidad
acceso abierto
Condiciones de uso
http://creativecommons.org/licenses/by/4.0/
Repositorio
SEDICI (UNLP)
Institución
Universidad Nacional de La Plata
OAI Identificador
oai:sedici.unlp.edu.ar:10915/55532
Acceder
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oai_identifier_str oai:sedici.unlp.edu.ar:10915/55532
network_acronym_str SEDICI
repository_id_str 1329
network_name_str SEDICI (UNLP)
spelling Flight path analysis in sounding rocket “Libertador I” with computational simulation on three degrees of freedomMurcia, J.Gomez, S.Cerón Muñoz, H.Portilla, G.Ingeniería AeronáuticaSimulacióntrayectoria de vuelorocket motorsolid propellantsounding rocketThis paper presents obtained results from computer simulations in order to analyze the flight path of the sounding rocket Libertador I, developed in 2012 at the Fundación Universitaria Los Libertadores. The main aspects that affect the motion of a rocket are propulsion and aerodynamics effects. Numerical algorithms were implemented to value the thrust provided by the rocket motor as well as aerodynamic loads. Then, the differential equations of the motion are solved using the Runge-Kutta method, RK9. Trajectory and other numerical results are calculated from a code developed in FORTRAN. Finally, graphs of the flight path, curves of the vehicle velocity as function of time are presented. Also, the algorithm permits to determine the maximum altitude and possible impact sites.Facultad de Ingeniería2014-11info:eu-repo/semantics/conferenceObjectinfo:eu-repo/semantics/publishedVersionObjeto de conferenciahttp://purl.org/coar/resource_type/c_5794info:ar-repo/semantics/documentoDeConferenciaapplication/pdfhttp://sedici.unlp.edu.ar/handle/10915/55532enginfo:eu-repo/semantics/altIdentifier/isbn/978-950-34-1152-0info:eu-repo/semantics/altIdentifier/url/http://www.aero.ing.unlp.edu.ar/caia/Actas-CAIA3/44.pdfinfo:eu-repo/semantics/openAccesshttp://creativecommons.org/licenses/by/4.0/Creative Commons Attribution 4.0 International (CC BY 4.0)reponame:SEDICI (UNLP)instname:Universidad Nacional de La Platainstacron:UNLP2025-10-22T16:47:15Zoai:sedici.unlp.edu.ar:10915/55532Institucionalhttp://sedici.unlp.edu.ar/Universidad públicaNo correspondehttp://sedici.unlp.edu.ar/oai/snrdalira@sedici.unlp.edu.arArgentinaNo correspondeNo correspondeNo correspondeopendoar:13292025-10-22 16:47:15.244SEDICI (UNLP) - Universidad Nacional de La Platafalse
dc.title.none.fl_str_mv Flight path analysis in sounding rocket “Libertador I” with computational simulation on three degrees of freedom
title Flight path analysis in sounding rocket “Libertador I” with computational simulation on three degrees of freedom
spellingShingle Flight path analysis in sounding rocket “Libertador I” with computational simulation on three degrees of freedom
Murcia, J.
Ingeniería Aeronáutica
Simulación
trayectoria de vuelo
rocket motor
solid propellant
sounding rocket
title_short Flight path analysis in sounding rocket “Libertador I” with computational simulation on three degrees of freedom
title_full Flight path analysis in sounding rocket “Libertador I” with computational simulation on three degrees of freedom
title_fullStr Flight path analysis in sounding rocket “Libertador I” with computational simulation on three degrees of freedom
title_full_unstemmed Flight path analysis in sounding rocket “Libertador I” with computational simulation on three degrees of freedom
title_sort Flight path analysis in sounding rocket “Libertador I” with computational simulation on three degrees of freedom
dc.creator.none.fl_str_mv Murcia, J.
Gomez, S.
Cerón Muñoz, H.
Portilla, G.
author Murcia, J.
author_facet Murcia, J.
Gomez, S.
Cerón Muñoz, H.
Portilla, G.
author_role author
author2 Gomez, S.
Cerón Muñoz, H.
Portilla, G.
author2_role author
author
author
dc.subject.none.fl_str_mv Ingeniería Aeronáutica
Simulación
trayectoria de vuelo
rocket motor
solid propellant
sounding rocket
topic Ingeniería Aeronáutica
Simulación
trayectoria de vuelo
rocket motor
solid propellant
sounding rocket
dc.description.none.fl_txt_mv This paper presents obtained results from computer simulations in order to analyze the flight path of the sounding rocket Libertador I, developed in 2012 at the Fundación Universitaria Los Libertadores. The main aspects that affect the motion of a rocket are propulsion and aerodynamics effects. Numerical algorithms were implemented to value the thrust provided by the rocket motor as well as aerodynamic loads. Then, the differential equations of the motion are solved using the Runge-Kutta method, RK9. Trajectory and other numerical results are calculated from a code developed in FORTRAN. Finally, graphs of the flight path, curves of the vehicle velocity as function of time are presented. Also, the algorithm permits to determine the maximum altitude and possible impact sites.
Facultad de Ingeniería
description This paper presents obtained results from computer simulations in order to analyze the flight path of the sounding rocket Libertador I, developed in 2012 at the Fundación Universitaria Los Libertadores. The main aspects that affect the motion of a rocket are propulsion and aerodynamics effects. Numerical algorithms were implemented to value the thrust provided by the rocket motor as well as aerodynamic loads. Then, the differential equations of the motion are solved using the Runge-Kutta method, RK9. Trajectory and other numerical results are calculated from a code developed in FORTRAN. Finally, graphs of the flight path, curves of the vehicle velocity as function of time are presented. Also, the algorithm permits to determine the maximum altitude and possible impact sites.
publishDate 2014
dc.date.none.fl_str_mv 2014-11
dc.type.none.fl_str_mv info:eu-repo/semantics/conferenceObject
info:eu-repo/semantics/publishedVersion
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http://purl.org/coar/resource_type/c_5794
info:ar-repo/semantics/documentoDeConferencia
format conferenceObject
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dc.identifier.none.fl_str_mv http://sedici.unlp.edu.ar/handle/10915/55532
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dc.language.none.fl_str_mv eng
language eng
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dc.rights.none.fl_str_mv info:eu-repo/semantics/openAccess
http://creativecommons.org/licenses/by/4.0/
Creative Commons Attribution 4.0 International (CC BY 4.0)
eu_rights_str_mv openAccess
rights_invalid_str_mv http://creativecommons.org/licenses/by/4.0/
Creative Commons Attribution 4.0 International (CC BY 4.0)
dc.format.none.fl_str_mv application/pdf
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repository.name.fl_str_mv SEDICI (UNLP) - Universidad Nacional de La Plata
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