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1. Identificação
Tipo de ReferênciaArtigo em Revista Científica (Journal Article)
Sitemtc-m16b.sid.inpe.br
Código do Detentorisadg {BR SPINPE} ibi 8JMKD3MGPCW/3DT298S
Identificador6qtX3pFwXQZGivnK2Y/Shwqd
Repositóriosid.inpe.br/mtc-m17@80/2007/11.27.17.30.15   (acesso restrito)
Última Atualização2007:11.27.17.46.35 (UTC) administrator
Repositório de Metadadossid.inpe.br/mtc-m17@80/2007/11.27.17.30.16
Última Atualização dos Metadados2021:02.11.18.12.05 (UTC) administrator
Chave SecundáriaINPE--PRE/
DOI10.1016/j.asr.2007.04.098
ISSN0273-1177
Chave de CitaçãoPradoFeli:2007:AnStPo
TítuloAn analytical study of the powered swing-by to perform orbital maneuvers
Ano2007
Data de Acesso28 abr. 2024
Tipo SecundárioPRE PI
Número de Arquivos1
Tamanho591 KiB
2. Contextualização
Autor1 Prado, Antonio Fernando Bertachini de Almeida
2 Felipe, Gislaine de
Identificador de Curriculo1 8JMKD3MGP5W/3C9JGJA
Grupo1 DMC-INPE-MCT-BR
2 DMC-INPE-MCT-BR
Afiliação1 Instituto Nacional de Pesquisas Espaciais (INPE)
2 Instituto Nacional de Pesquisas Espaciais (INPE)
RevistaAdvances in Space Research
Volume40
Número12
Páginas1769-1968
Histórico (UTC)2007-11-27 18:03:27 :: marciana -> administrator ::
2010-05-11 02:11:49 :: administrator -> marciana ::
2011-05-20 22:30:43 :: marciana -> administrator ::
2021-02-11 18:12:05 :: administrator -> marciana :: 2007
3. Conteúdo e estrutura
É a matriz ou uma cópia?é a matriz
Estágio do Conteúdoconcluido
Transferível1
Tipo do ConteúdoExternal Contribution
Palavras-ChaveAstrodynamics
Swing-by
Orbital maneuvers
Patched-conics approximation
ResumoIn the present paper, we present an analytical description of the powered swing-by maneuver in the three-dimensional space. To perform this task, new analytical equations are derived for the three-dimensional unpowered swing-by, including the variation in velocity, angular momentum, energy and inclination of the spacecraft due to the maneuver. This is done based on the patched-conics approximation. From those general three-dimensional equations, it is possible to confirm some well-known analytical results for the planar case. The equations developed here are verified by numerical integrations, using the restricted problem of three bodies, showing an agreement better than 1%. After that, based on those equations, some new analytical results are obtained for the situation when an impulse is applied to the spacecraft during the close approach. Those new equations are based in the assumption that the impulse applied is small compared to the velocity of the spacecraft, and they allow the calculation of the same variations cited above. Those equations can be simplified for specific cases, and it can generate some conclusions about the direction to apply the impulse to attend specific goals. A study is also executed to investigate in which cases the impulse is more efficient when applied at the periapsis of the swing-by hyperbola or at points far way from the swing-by body.
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4. Condições de acesso e uso
Idiomaen
Arquivo Alvoprado3.pdf
Grupo de Usuáriosadministrator
marciana
Visibilidadeshown
Política de Arquivamentodenypublisher denyfinaldraft24
Permissão de Leituradeny from all and allow from 150.163
5. Fontes relacionadas
Unidades Imediatamente Superiores8JMKD3MGPCW/446AF4B
DivulgaçãoWEBSCI; PORTALCAPES; MGA; COMPENDEX.
Acervo Hospedeirolcp.inpe.br/ignes/2004/02.12.18.39
cptec.inpe.br/walmeida/2003/04.25.17.12
6. Notas
Campos Vaziosalternatejournal archivist callnumber copyholder copyright creatorhistory descriptionlevel documentstage e-mailaddress electronicmailaddress format isbn label lineage mark mirrorrepository month 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
e-Mail (login)marciana
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