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1. Identificação
Tipo de ReferênciaArtigo em Revista Científica (Journal Article)
Sitemtc-m21b.sid.inpe.br
Código do Detentorisadg {BR SPINPE} ibi 8JMKD3MGPCW/3DT298S
Identificador8JMKD3MGP3W34P/3PUFH55
Repositóriosid.inpe.br/mtc-m21b/2017/11.07.15.05   (acesso restrito)
Última Atualização2017:11.07.15.05.05 (UTC) administrator
Repositório de Metadadossid.inpe.br/mtc-m21b/2017/11.07.15.05.05
Última Atualização dos Metadados2021:02.11.18.12.52 (UTC) administrator
DOI10.1007/s10509-017-3177-x
ISSN0004-640X
Chave de CitaçãoSantosPradMerg:2017:LiSpAr
TítuloLifetime of a spacecraft around a synchronous system of asteroids using a dipole model
Ano2017
MêsNov.
Data de Acesso17 maio 2024
Tipo de Trabalhojournal article
Tipo SecundárioPRE PI
Número de Arquivos1
Tamanho3578 KiB
2. Contextualização
Autor1 Santos, Leonardo Barbosa Torres dos
2 Prado, Antonio Fernando Bertachini de Almeida
3 Merguizo Sanchez, Diogo
Identificador de Curriculo1
2 8JMKD3MGP5W/3C9JGJA
Grupo1 CMC-ETES-SESPG-INPE-MCTIC-GOV-BR
2 DIDMC-CGETE-INPE-MCTIC-GOV-BR
3 DIDMC-CGETE-INPE-MCTIC-GOV-BR
Afiliação1 Instituto Nacional de Pesquisas Espaciais (INPE)
2 Instituto Nacional de Pesquisas Espaciais (INPE)
3 Instituto Nacional de Pesquisas Espaciais (INPE)
Endereço de e-Mail do Autor1 leonardo.btorres@inpe.br
2 antonio.prado@inpe.br
3 diogo.sanchez@inpe.br
RevistaAstrophysics and Space Science
Volume362
Número11
Nota SecundáriaB1_GEOCIÊNCIAS B3_MATEMÁTICA_/_PROBABILIDADE_E_ESTATÍSTICA B3_ASTRONOMIA_/_FÍSICA
Histórico (UTC)2017-11-07 15:05:05 :: simone -> administrator ::
2017-11-07 15:05:06 :: administrator -> simone :: 2017
2017-11-07 15:05:34 :: simone -> administrator :: 2017
2017-11-21 07:39:18 :: administrator -> simone :: 2017
2017-12-11 16:32:58 :: simone -> administrator :: 2017
2021-02-11 18:12:52 :: administrator -> simone :: 2017
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-ChaveCelestial mechanics
Minor planets asteroid
Restricted synchronous four-body problem
ResumoSpace missions allow us to expand our knowledge about the origin of the solar system. It is believed that asteroids and comets preserve the physical characteristics from the time that the solar system was created. For this reason, there was an increase of missions to asteroids in the past few years. To send spacecraft to asteroids or comets is challenging, since these objects have their own characteristics in several aspects, such as size, shape, physical properties, etc., which are often only discovered after the approach and even after the landing of the spacecraft. These missions must be developed with sufficient flexibility to adjust to these parameters, which are better determined only when the spacecraft reaches the system. Therefore, conducting a dynamic investigation of a spacecraft around a multiple asteroid system offers an extremely rich environment. Extracting accurate information through analytical approaches is quite challenging and requires a significant number of restrictive assumptions. For this reason, a numerical approach to the dynamics of a spacecraft in the vicinity of a binary asteroid system is offered in this paper. In the present work, the equations of the Restricted Synchronous Four- Body Problem (RSFBP) are used to model a binary asteroid system. The main objective of this work is to construct grids of initial conditions, which relates semi- major axis and eccentricity, in order to quantify the lifetime of a spacecraft when released close to the less massive body of the binary system (modeled as a rotating mass dipole). We performed an analysis of the lifetime of the spacecraft considering several mass ratios of a binary system of asteroids and investigating the behavior of a spacecraft in the vicinity of this system. We analyze direct and retrograde orbits. This study investigated orbits that survive for at least 500 orbital periods of the system (which is approximately one year), then not colliding or escaping from the system during this time. In this work, we take into account the gravitational forces of the binary asteroid system and the solar radiation pressure (SRP). We found several regions where the direct and retrograde orbits of a spacecraft survive throughout the integration time (one year) when the solar radiation pressure is taken into account. Numerical evidence shows that retrograde orbits have a larger region initial conditions that generate orbits that survive for one year, compared to direct orbits.
ÁreaETES
Arranjo 1urlib.net > BDMCI > Fonds > Produção pgr ATUAIS > CMC > Lifetime of a...
Arranjo 2urlib.net > BDMCI > Fonds > Produção anterior à 2021 > DIDMC > Lifetime of a...
Conteúdo da Pasta docacessar
Conteúdo da Pasta sourcenão têm arquivos
Conteúdo da Pasta agreement
agreement.html 07/11/2017 13:05 1.0 KiB 
4. Condições de acesso e uso
Idiomaen
Arquivo Alvosantos_lifetime.pdf
Grupo de Usuáriossimone
Grupo de Leitoresadministrator
simone
Visibilidadeshown
Política de Arquivamentodenypublisher denyfinaldraft12
Permissão de Leituradeny from all and allow from 150.163
Permissão de Atualizaçãonão transferida
5. Fontes relacionadas
Vinculação8JMKD3MGP3W34P/3HQHJ72
Repositório Espelhosid.inpe.br/mtc-m21b/2013/09.26.14.25.22
Unidades Imediatamente Superiores8JMKD3MGPCW/3F2UALS
8JMKD3MGPCW/446AF4B
Lista de Itens Citandosid.inpe.br/bibdigital/2021/02.11.18.06 2
sid.inpe.br/mtc-m21/2012/07.13.14.40.20 1
sid.inpe.br/bibdigital/2013/10.14.00.13 1
DivulgaçãoWEBSCI; PORTALCAPES.
Acervo Hospedeirosid.inpe.br/mtc-m21b/2013/09.26.14.25.20
6. Notas
Campos Vaziosalternatejournal archivist callnumber copyholder copyright creatorhistory descriptionlevel e-mailaddress format isbn label lineage mark nextedition notes orcid pages parameterlist parentrepositories previousedition previouslowerunit progress project rightsholder schedulinginformation secondarydate secondarykey session shorttitle sponsor subject tertiarytype url
7. Controle da descrição
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