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1. Identificação
Tipo de ReferênciaArtigo em Revista Científica (Journal Article)
Sitemtc-m21c.sid.inpe.br
Código do Detentorisadg {BR SPINPE} ibi 8JMKD3MGPCW/3DT298S
Identificador8JMKD3MGP3W34R/43MHJ9L
Repositóriosid.inpe.br/mtc-m21c/2020/12.01.13.33   (acesso restrito)
Última Atualização2020:12.01.13.33.17 (UTC) simone
Repositório de Metadadossid.inpe.br/mtc-m21c/2020/12.01.13.33.17
Última Atualização dos Metadados2022:01.04.01.35.39 (UTC) administrator
DOI10.1007/s11071-020-05992-x
ISSN0924-090X
Chave de CitaçãoFerreiraMoraPradWint:2020:MaStTe
TítuloA mathematical study of the tethered slingshot maneuver using the elliptic restricted problem
Ano2020
Data de Acesso06 maio 2024
Tipo de Trabalhojournal article
Tipo SecundárioPRE PI
Número de Arquivos1
Tamanho3348 KiB
2. Contextualização
Autor1 Ferreira, Alessandra Ferraz da Silva
2 Moraes, Rodolpho Vilhena de
3 Prado, Antonio Fernando Bertachini de Almeida
4 Winter, Othon C.
Identificador de Curriculo1
2
3 8JMKD3MGP5W/3C9JGJA
ORCID1 0000-0002-6162-9078
2 0000-0003-1289-8332
3 0000-0002-7966-3231
4 0000-0002-4901-3289
Grupo1
2
3 DIDMC-CGETE-INPE-MCTIC-GOV-BR
Afiliação1 Universidade Estadual Paulista (UNESP)
2 Universidade Estadual Paulista (UNESP)
3 Instituto Nacional de Pesquisas Espaciais (INPE)
4 Universidade Estadual Paulista (UNESP)
Endereço de e-Mail do Autor1 aleferrazsilva@hotmail.com
2 rodolpho.vilhena@gmail.com
3 antonio.prado@inpe.br
4 othon.winter@unesp.br
RevistaNonlinear Dynamics
Volume102
Páginas1585-1609
Nota SecundáriaA2_INTERDISCIPLINAR A2_ENGENHARIAS_III A2_ENGENHARIAS_I B1_MATEMÁTICA_/_PROBABILIDADE_E_ESTATÍSTICA B1_ENGENHARIAS_IV B1_ENGENHARIAS_II B3_ASTRONOMIA_/_FÍSICA
Histórico (UTC)2020-12-01 13:33:17 :: simone -> administrator ::
2020-12-01 13:33:18 :: administrator -> simone :: 2020
2020-12-14 13:40:05 :: simone -> administrator :: 2020
2022-01-04 01:35:39 :: administrator -> simone :: 2020
3. Conteúdo e estrutura
É a matriz ou uma cópia?é a matriz
Estágio do Conteúdoconcluido
Transferível1
Tipo do ConteúdoExternal Contribution
Tipo de Versãopublisher
Palavras-ChaveAstrodynamics Tethered slingshot maneuver Tether Spacecraft Orbital maneuvers Energy variation
ResumoThe main objective of the present paper is to find the modifications that a tethered slingshot maneuver (TSSM) can make in the orbit of a spacecraft, both in terms of energy and inclination. The TSSM is a maneuver where a tether fixed in a celestial body, like a moon or an asteroid, makes a rotation in the velocity vector of a spacecraft to modify its orbit. In particular, the present paper concentrates in showing the potential savings in fuel consumption for orbital maneuvers that use this technique in an elliptic system of primaries, which gives advantages over the circular problem. To make this study more complete, analytical approximations are derived to provide a general view of the behavior of the maneuver in terms of variations of energy and inclination as a function of different conditions for the geometry, length, and location of the tether. Among the main results, it is showed the best location to place the tether and the best moment and duration to perform the maneuver, as a function of the parameters involved, like the orbits of the primaries, the incoming velocity of the spacecraft, etc. The solutions are shown in maps giving the variations of energy and inclination for different locations of this device and assuming different incoming orbits for the spacecraft. Regions that maximize those variations are indicated. Based on those results, it is possible to find the best solution for several particular problems. The results show that this maneuver has a large potential to be explored, helping a spacecraft to make journeys to the exterior planets and out of the Solar System. Those results are arguments in favor of developing efforts to solve the technological problems involved in real applications of this technique. The main advantage of the proposed technique is the energy gain given by the maneuver, in particular when using the higher velocity of the asteroid, at the periapsis of its orbit around the Sun. The main disadvantages are the technical challenges involved in the implementation of the maneuver and the fact that to get maximum benefits, there are time restrictions to apply the maneuver, because the asteroid must be passing by its periapsis.
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4. Condições de acesso e uso
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Arquivo AlvoFerreira2020_Article_AMathematicalStudyOfTheTethere.pdf
Grupo de Usuáriossimone
Grupo de Leitoresadministrator
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Visibilidadeshown
Política de Arquivamentodenypublisher denyfinaldraft12
Permissão de Leituradeny from all and allow from 150.163
Permissão de Atualizaçãonão transferida
5. Fontes relacionadas
Unidades Imediatamente Superiores8JMKD3MGPCW/446AF4B
Lista de Itens Citandosid.inpe.br/bibdigital/2021/02.11.18.06 4
sid.inpe.br/mtc-m21/2012/07.13.14.40.20 1
DivulgaçãoWEBSCI; PORTALCAPES.
Acervo Hospedeirourlib.net/www/2017/11.22.19.04
6. Notas
Campos Vaziosalternatejournal archivist callnumber copyholder copyright creatorhistory descriptionlevel e-mailaddress format isbn label lineage mark mirrorrepository month nextedition notes number parameterlist parentrepositories previousedition previouslowerunit progress project rightsholder schedulinginformation secondarydate secondarykey session shorttitle sponsor subject tertiarymark tertiarytype url
7. Controle da descrição
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