Controlling the Eccentricity of Polar Lunar Orbits with Low-Thrust Propulsion

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dc.contributor.authorWinter, O. C. [UNESP]
dc.contributor.authorMourao, D. C. [UNESP]
dc.contributor.authorMelo, C. F. [UNESP]
dc.contributor.authorMacau, E. N.
dc.contributor.authorFerreira, J. L.
dc.contributor.authorCarvalho, J. P. S. [UNESP]
dc.contributor.institutionUniversidade Estadual Paulista (Unesp)
dc.contributor.institutionInstituto Nacional de Pesquisas Espaciais (INPE)
dc.contributor.institutionUniversidade de Brasília (UnB)
dc.date.accessioned2014-05-20T15:33:56Z
dc.date.available2014-05-20T15:33:56Z
dc.date.issued2009-01-01
dc.description.abstractIt 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.en
dc.description.affiliationUniv Estadual Paulista, UNESP, Grp Dinam Orbital & Planetol, BR-12516410 Guaratingueta, SP, Brazil
dc.description.affiliationINPE, Sao Jose Dos Campos, SP, Brazil
dc.description.affiliationUniv Brasilia UnB, Inst Fis, BR-70919970 Brasilia, DF, Brazil
dc.description.affiliationUnespUniv Estadual Paulista, UNESP, Grp Dinam Orbital & Planetol, BR-12516410 Guaratingueta, SP, Brazil
dc.description.sponsorshipConselho Nacional de Desenvolvimento Científico e Tecnológico (CNPq)
dc.description.sponsorshipFundação de Amparo à Pesquisa do Estado de São Paulo (FAPESP)
dc.description.sponsorshipAgência Espacial Brasileira (AEB)
dc.format.extent10
dc.identifierhttp://dx.doi.org/10.1155/2009/159287
dc.identifier.citationMathematical Problems In Engineering. New York: Hindawi Publishing Corporation, p. 10, 2009.
dc.identifier.doi10.1155/2009/159287
dc.identifier.fileWOS000277590300001.pdf
dc.identifier.issn1024-123X
dc.identifier.lattes0960024575647258
dc.identifier.urihttp://hdl.handle.net/11449/42366
dc.identifier.wosWOS:000277590300001
dc.language.isoeng
dc.publisherHindawi Publishing Corporation
dc.relation.ispartofMathematical Problems in Engineering
dc.relation.ispartofjcr1.145
dc.rights.accessRightsAcesso aberto
dc.sourceWeb of Science
dc.titleControlling the Eccentricity of Polar Lunar Orbits with Low-Thrust Propulsionen
dc.typeArtigo
dcterms.licensehttp://www.hindawi.com/journals/apm/apc/
dcterms.rightsHolderHindawi Publishing Corporation
unesp.author.lattes0960024575647258
unesp.campusUniversidade Estadual Paulista (Unesp), Faculdade de Engenharia, Guaratinguetápt
unesp.departmentMatemática - FEGpt

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Guaratinguetá - FEG - Faculdade de Engenharia e Ciências