Orbital maneuvers using gravitational capture times

Página do item simplificado
dc.contributor.authorWinter, O. C.
dc.contributor.authorNeto, E. V.
dc.contributor.authorPrado, AFBA
dc.contributor.institutionUniversidade Estadual Paulista (Unesp)
dc.contributor.institutionInstituto Nacional de Pesquisas Espaciais (INPE)
dc.date.accessioned2014-05-20T15:24:13Z
dc.date.available2014-05-20T15:24:13Z
dc.date.issued2003-01-01
dc.description.abstractArtificial satellites around the Earth can be temporarily captured by the Moon via gravitational mechanisms., How long the capture remains depends on the phase space region where the trajectory is located. This interval of time (capture time) ranges from less than one day (a single passage), up to 500 days, or even more. Orbits of longer times might be very useful for certain types of missions. The advantage of the ballistic capture is to save fuel consumption in an orbit transference from around the Earth to around the Moon. Some of the impulse needed in the transference is saved by the use of the gravitational forces involved. However, the time needed for the transference is elongated from days to months. In the present work we have mapped a significant part of the phase space of the Earth-Moon system, determining the length of the capture times and the origin of the trajectory, if it comes from the Earth direction, or from the opposite direction. Using such map we present a set of missions considering the utilization of the long capture times. (C) 2003 COSPAR. Published by Elsevier B.V. Ltd. All rights reserved.en
dc.description.affiliationUNESP, Grp Dinam Orbital & Planetol, BR-12500000 Guaratingueta, SP, Brazil
dc.description.affiliationINPE, Div Mecan Espacial & Controle, BR-12227010 Sao Jose Dos Campos, Brazil
dc.description.affiliationUnespUNESP, Grp Dinam Orbital & Planetol, BR-12500000 Guaratingueta, SP, Brazil
dc.format.extent2005-2010
dc.identifierhttp://dx.doi.org/10.1016/S0273-1177(03)00176-5
dc.identifier.citationIntegrated Space Geodetic Systems and Satellite Dynamics. Kidlington: Pergamon-Elsevier B.V., v. 31, n. 8, p. 2005-2010, 2003.
dc.identifier.doi10.1016/S0273-1177(03)00176-5
dc.identifier.issn0273-1177
dc.identifier.lattes0960024575647258
dc.identifier.urihttp://hdl.handle.net/11449/34864
dc.identifier.wosWOS:000184780400021
dc.language.isoeng
dc.publisherElsevier B.V.
dc.relation.ispartofIntegrated Space Geodetic Systems and Satellite Dynamics
dc.relation.ispartofjcr1.529
dc.relation.ispartofsjr0,569
dc.rights.accessRightsAcesso restrito
dc.sourceWeb of Science
dc.titleOrbital maneuvers using gravitational capture timesen
dc.typeArtigo
dcterms.licensehttp://www.elsevier.com/about/open-access/open-access-policies/article-posting-policy
dcterms.rightsHolderElsevier B.V.
unesp.author.lattes0960024575647258
unesp.campusUniversidade Estadual Paulista (Unesp), Faculdade de Engenharia, Guaratinguetápt

Arquivos

Licença do Pacote
Agora exibindo 1 - 1 de 1
Nenhuma Miniatura disponível
Nome:
license.txt
Tamanho:
1.71 KB
Formato:
Item-specific license agreed upon to submission
Descrição:

Coleções

Artigos - Matemática - FEG