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1. Identificação
Tipo de ReferênciaArtigo em Revista Científica (Journal Article)
Sitemtc-m16c.sid.inpe.br
Código do Detentorisadg {BR SPINPE} ibi 8JMKD3MGPCW/3DT298S
Identificador8JMKD3MGP8W/35HKSPP
Repositóriosid.inpe.br/mtc-m18@80/2009/06.26.14.32   (acesso restrito)
Última Atualização2009:06.26.14.32.25 (UTC) administrator
Repositório de Metadadossid.inpe.br/mtc-m18@80/2009/06.26.14.32.27
Última Atualização dos Metadados2020:04.28.17.48.42 (UTC) administrator
Chave SecundáriaINPE--PRE/
DOI10.1007/s10569-009-9193-6
ISSN0923-2958
Chave de CitaçãoMeloMacaWint:2009:StPlCh
TítuloStrategies for plane change of Earth orbits using lunar gravity and derived trajectories of family G
Ano2009
MêsApr.
Data de Acesso19 maio 2024
Tipo SecundárioPRE PI
Número de Arquivos1
Tamanho639 KiB
2. Contextualização
Autor1 Melo, Cristian Fiorilo
2 Macau, Elbert Einstein Nehrer
3 Winter, O. C.
Identificador de Curriculo1
2 8JMKD3MGP5W/3C9JGUT
Grupo1 LAC-CTE-INPE-MCT-BR
2 LAC-CTE-INPE-MCT-BR
Afiliação1 Instituto Nacional de Pesquisas Espaciais (INPE)
2 Instituto Nacional de Pesquisas Espaciais (INPE)
RevistaCelestial Mechanics and Dynamical Astronomy
Volume103
Número4
Páginas281-299
Histórico (UTC)2009-06-26 14:32:52 :: simone -> administrator ::
2010-05-11 01:08:39 :: administrator -> simone ::
2011-05-20 20:51:55 :: simone -> administrator ::
2020-04-28 17:48:42 :: administrator -> simone :: 2009
3. Conteúdo e estrutura
É a matriz ou uma cópia?é a matriz
Estágio do Conteúdoconcluido
Transferível1
Tipo do ConteúdoExternal Contribution
Palavras-ChaveAstrodynamics
Earth-Moon system
Mission design
Orbital maneuvers
Swing-by
Gravity assisted maneuver
ResumoThe dynamics of the circular restricted three-body Earth-Moon-particle problem predicts the existence of the retrograde periodic orbits around the Lagrangian equilibrium point L1. Such orbits belong to the so-called family G (Broucke, Periodic orbits in the restricted three-body problem with Earth-Moon masses, JPL Technical Report 32-1168, 1968) and starting from them it is possible to define a set of trajectories that form round trip links between the Earth and the Moon. These links occur even with more complex dynamical systems as the complete Sun-Earth-Moon-particle problem. One of the most remarkable properties of these trajectories, observed for the four-body problem, is a meaningful inclination gain when they penetrate into the lunar sphere of influence and accomplish a swing-by with the Moon. This way, when one of these trajectories returns to the proximities of the Earth, it will be in a different orbital plane from its initial Earth orbit. In this work, we present studies that show the possibility of using this property mainly to accomplish transfer maneuvers between two Earth orbits with different altitudes and inclinations, with low cost, taking into account the dynamics of the four-body problem and of the swing-by as well. The results show that it is possible to design a set of nominal transfer trajectories that require Delta V (Total) less than conventional methods like Hohmann, bi-elliptic and bi-parabolic transfer with plane change.
ÁreaCOMP
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Conteúdo da Pasta docacessar
Conteúdo da Pasta sourcenão têm arquivos
Conteúdo da Pasta agreementnão têm arquivos
4. Condições de acesso e uso
Idiomaen
Arquivo Alvostrategies for plane.pdf
Grupo de Usuáriosadministrator
simone
Visibilidadeshown
Política de Arquivamentodenypublisher denyfinaldraft12
Permissão de Leituradeny from all and allow from 150.163
5. Fontes relacionadas
Repositório Espelhosid.inpe.br/mtc-m18@80/2008/03.17.15.17.24
Unidades Imediatamente Superiores8JMKD3MGPCW/3ESGTTP
DivulgaçãoWEBSCI
Acervo Hospedeirosid.inpe.br/mtc-m18@80/2008/03.17.15.17
6. Notas
Campos Vaziosalternatejournal archivist callnumber copyholder copyright creatorhistory descriptionlevel documentstage e-mailaddress electronicmailaddress format isbn label lineage mark nextedition notes orcid parameterlist parentrepositories previousedition previouslowerunit progress project readergroup rightsholder schedulinginformation secondarydate secondarymark session shorttitle sponsor subject tertiarymark tertiarytype typeofwork url versiontype
7. Controle da descrição
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