Controlling the Eccentricity of Polar Lunar Orbits with Low-Thrust Propulsion
Autor(a) principal: | |
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Data de Publicação: | 2009 |
Outros Autores: | , , , , |
Tipo de documento: | Artigo |
Idioma: | eng |
Título da fonte: | Repositório Institucional da UNESP |
Texto Completo: | http://dx.doi.org/10.1155/2009/159287 http://hdl.handle.net/11449/42366 |
Resumo: | It is well known that lunar satellites in polar orbits suffer a high increase on the eccentricity due to the gravitational perturbation of the Earth. That effect is a natural consequence of the Lidov-Kozai resonance. The final fate of such satellites is the collision with the Moon. Therefore, the control of the orbital eccentricity leads to the control of the satellite's lifetime. In the present work we study this problem and introduce an approach in order to keep the orbital eccentricity of the satellite at low values. The whole work was made considering two systems: the 3-body problem, Moon-Earth-satellite, and the 4-body problem, Moon-Earth-Sun-satellite. First, we simulated the systems considering a satellite with initial eccentricity equals to 0.0001 and a range of initial altitudes between 100 km and 5000 km. In such simulations we followed the evolution of the satellite's eccentricity. We also obtained an empirical expression for the length of time needed to occur the collision with the Moon as a function of the initial altitude. The results found for the 3-body model were not significantly different from those found for the 4-body model. Secondly, using low-thrust propulsion, we introduced a correction of the eccentricity every time it reached the value 0.05. These simulations were made considering a set of different thrust values, from 0.1N up to 0.4N which can be obtained by using Hall Plasma Thrusters. In each run we measured the length of time, needed to correct the eccentricity value (from e = 0.04 to e = 0.05). From these results we obtained empirical expressions of this time as a function of the initial altitude and as a function of the thrust value. Copyright (C) 2009 O. C. Winter et al. |
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Controlling the Eccentricity of Polar Lunar Orbits with Low-Thrust PropulsionIt is well known that lunar satellites in polar orbits suffer a high increase on the eccentricity due to the gravitational perturbation of the Earth. That effect is a natural consequence of the Lidov-Kozai resonance. The final fate of such satellites is the collision with the Moon. Therefore, the control of the orbital eccentricity leads to the control of the satellite's lifetime. In the present work we study this problem and introduce an approach in order to keep the orbital eccentricity of the satellite at low values. The whole work was made considering two systems: the 3-body problem, Moon-Earth-satellite, and the 4-body problem, Moon-Earth-Sun-satellite. First, we simulated the systems considering a satellite with initial eccentricity equals to 0.0001 and a range of initial altitudes between 100 km and 5000 km. In such simulations we followed the evolution of the satellite's eccentricity. We also obtained an empirical expression for the length of time needed to occur the collision with the Moon as a function of the initial altitude. The results found for the 3-body model were not significantly different from those found for the 4-body model. Secondly, using low-thrust propulsion, we introduced a correction of the eccentricity every time it reached the value 0.05. These simulations were made considering a set of different thrust values, from 0.1N up to 0.4N which can be obtained by using Hall Plasma Thrusters. In each run we measured the length of time, needed to correct the eccentricity value (from e = 0.04 to e = 0.05). From these results we obtained empirical expressions of this time as a function of the initial altitude and as a function of the thrust value. Copyright (C) 2009 O. C. Winter et al.Conselho Nacional de Desenvolvimento Científico e Tecnológico (CNPq)Fundação de Amparo à Pesquisa do Estado de São Paulo (FAPESP)Agência Espacial Brasileira (AEB)Univ Estadual Paulista, UNESP, Grp Dinam Orbital & Planetol, BR-12516410 Guaratingueta, SP, BrazilINPE, Sao Jose Dos Campos, SP, BrazilUniv Brasilia UnB, Inst Fis, BR-70919970 Brasilia, DF, BrazilUniv Estadual Paulista, UNESP, Grp Dinam Orbital & Planetol, BR-12516410 Guaratingueta, SP, BrazilHindawi Publishing CorporationUniversidade Estadual Paulista (Unesp)Instituto Nacional de Pesquisas Espaciais (INPE)Universidade de Brasília (UnB)Winter, O. C. [UNESP]Mourao, D. C. [UNESP]Melo, C. F. [UNESP]Macau, E. N.Ferreira, J. L.Carvalho, J. P. S. [UNESP]2014-05-20T15:33:56Z2014-05-20T15:33:56Z2009-01-01info:eu-repo/semantics/publishedVersioninfo:eu-repo/semantics/article10application/pdfhttp://dx.doi.org/10.1155/2009/159287Mathematical Problems In Engineering. New York: Hindawi Publishing Corporation, p. 10, 2009.1024-123Xhttp://hdl.handle.net/11449/4236610.1155/2009/159287WOS:000277590300001WOS000277590300001.pdf0960024575647258Web of Sciencereponame:Repositório Institucional da UNESPinstname:Universidade Estadual Paulista (UNESP)instacron:UNESPengMathematical Problems in Engineering1.145info:eu-repo/semantics/openAccess2023-12-03T06:12:06Zoai:repositorio.unesp.br:11449/42366Repositório InstitucionalPUBhttp://repositorio.unesp.br/oai/requestopendoar:29462023-12-03T06:12:06Repositório Institucional da UNESP - Universidade Estadual Paulista (UNESP)false |
dc.title.none.fl_str_mv |
Controlling the Eccentricity of Polar Lunar Orbits with Low-Thrust Propulsion |
title |
Controlling the Eccentricity of Polar Lunar Orbits with Low-Thrust Propulsion |
spellingShingle |
Controlling the Eccentricity of Polar Lunar Orbits with Low-Thrust Propulsion Winter, O. C. [UNESP] |
title_short |
Controlling the Eccentricity of Polar Lunar Orbits with Low-Thrust Propulsion |
title_full |
Controlling the Eccentricity of Polar Lunar Orbits with Low-Thrust Propulsion |
title_fullStr |
Controlling the Eccentricity of Polar Lunar Orbits with Low-Thrust Propulsion |
title_full_unstemmed |
Controlling the Eccentricity of Polar Lunar Orbits with Low-Thrust Propulsion |
title_sort |
Controlling the Eccentricity of Polar Lunar Orbits with Low-Thrust Propulsion |
author |
Winter, O. C. [UNESP] |
author_facet |
Winter, O. C. [UNESP] Mourao, D. C. [UNESP] Melo, C. F. [UNESP] Macau, E. N. Ferreira, J. L. Carvalho, J. P. S. [UNESP] |
author_role |
author |
author2 |
Mourao, D. C. [UNESP] Melo, C. F. [UNESP] Macau, E. N. Ferreira, J. L. Carvalho, J. P. S. [UNESP] |
author2_role |
author author author author author |
dc.contributor.none.fl_str_mv |
Universidade Estadual Paulista (Unesp) Instituto Nacional de Pesquisas Espaciais (INPE) Universidade de Brasília (UnB) |
dc.contributor.author.fl_str_mv |
Winter, O. C. [UNESP] Mourao, D. C. [UNESP] Melo, C. F. [UNESP] Macau, E. N. Ferreira, J. L. Carvalho, J. P. S. [UNESP] |
description |
It is well known that lunar satellites in polar orbits suffer a high increase on the eccentricity due to the gravitational perturbation of the Earth. That effect is a natural consequence of the Lidov-Kozai resonance. The final fate of such satellites is the collision with the Moon. Therefore, the control of the orbital eccentricity leads to the control of the satellite's lifetime. In the present work we study this problem and introduce an approach in order to keep the orbital eccentricity of the satellite at low values. The whole work was made considering two systems: the 3-body problem, Moon-Earth-satellite, and the 4-body problem, Moon-Earth-Sun-satellite. First, we simulated the systems considering a satellite with initial eccentricity equals to 0.0001 and a range of initial altitudes between 100 km and 5000 km. In such simulations we followed the evolution of the satellite's eccentricity. We also obtained an empirical expression for the length of time needed to occur the collision with the Moon as a function of the initial altitude. The results found for the 3-body model were not significantly different from those found for the 4-body model. Secondly, using low-thrust propulsion, we introduced a correction of the eccentricity every time it reached the value 0.05. These simulations were made considering a set of different thrust values, from 0.1N up to 0.4N which can be obtained by using Hall Plasma Thrusters. In each run we measured the length of time, needed to correct the eccentricity value (from e = 0.04 to e = 0.05). From these results we obtained empirical expressions of this time as a function of the initial altitude and as a function of the thrust value. Copyright (C) 2009 O. C. Winter et al. |
publishDate |
2009 |
dc.date.none.fl_str_mv |
2009-01-01 2014-05-20T15:33:56Z 2014-05-20T15:33:56Z |
dc.type.status.fl_str_mv |
info:eu-repo/semantics/publishedVersion |
dc.type.driver.fl_str_mv |
info:eu-repo/semantics/article |
format |
article |
status_str |
publishedVersion |
dc.identifier.uri.fl_str_mv |
http://dx.doi.org/10.1155/2009/159287 Mathematical Problems In Engineering. New York: Hindawi Publishing Corporation, p. 10, 2009. 1024-123X http://hdl.handle.net/11449/42366 10.1155/2009/159287 WOS:000277590300001 WOS000277590300001.pdf 0960024575647258 |
url |
http://dx.doi.org/10.1155/2009/159287 http://hdl.handle.net/11449/42366 |
identifier_str_mv |
Mathematical Problems In Engineering. New York: Hindawi Publishing Corporation, p. 10, 2009. 1024-123X 10.1155/2009/159287 WOS:000277590300001 WOS000277590300001.pdf 0960024575647258 |
dc.language.iso.fl_str_mv |
eng |
language |
eng |
dc.relation.none.fl_str_mv |
Mathematical Problems in Engineering 1.145 |
dc.rights.driver.fl_str_mv |
info:eu-repo/semantics/openAccess |
eu_rights_str_mv |
openAccess |
dc.format.none.fl_str_mv |
10 application/pdf |
dc.publisher.none.fl_str_mv |
Hindawi Publishing Corporation |
publisher.none.fl_str_mv |
Hindawi Publishing Corporation |
dc.source.none.fl_str_mv |
Web of Science reponame:Repositório Institucional da UNESP instname:Universidade Estadual Paulista (UNESP) instacron:UNESP |
instname_str |
Universidade Estadual Paulista (UNESP) |
instacron_str |
UNESP |
institution |
UNESP |
reponame_str |
Repositório Institucional da UNESP |
collection |
Repositório Institucional da UNESP |
repository.name.fl_str_mv |
Repositório Institucional da UNESP - Universidade Estadual Paulista (UNESP) |
repository.mail.fl_str_mv |
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1799965153576353792 |