| 1. Identificação | |
| Tipo de Referência | Artigo em Revista Científica (Journal Article) |
| Site | plutao.sid.inpe.br |
| Código do Detentor | isadg {BR SPINPE} ibi 8JMKD3MGPCW/3DT298S |
| Identificador | J8LNKAN8RW/34BER8B |
| Repositório | dpi.inpe.br/plutao@80/2008/12.04.12.20.06 (acesso restrito) |
| Última Atualização | 2013:02.06.15.59.17 (UTC) marciana |
| Repositório de Metadados | dpi.inpe.br/plutao@80/2008/12.04.12.20.07 |
| Última Atualização dos Metadados | 2021:02.11.18.11.17 (UTC) administrator |
| DOI | 10.1016/j.actaastro.2008.05.005 |
| ISSN | 0094-5765 |
| Rótulo | lattes: 7340081273816424 2 CabettePrad:2008:TrOrTo |
| Chave de Citação | SantosCabettePrad:2008:TrOrTo |
| Título | Transfer orbits to/from the Lagrangian points in the restricted four-body problem  |
| Ano | 2008 |
| Data de Acesso | 05 maio 2024 |
| Tipo Secundário | PRE PI |
| Número de Arquivos | 1 |
| Tamanho | 489 KiB |
| 2. Contextualização | |
| Autor | 1 Santos Cabette, Regina Elaine 2 Prado, Antonio Fernando Bertachini de Almeida |
| Grupo | 1 2 DMC-ETE-INPE-MCT-BR |
| Afiliação | 1 2 Instituto Nacional de Pesquisas Espaciais (INPE) |
| Endereço de e-Mail do Autor | 1 2 abertachini@terra.com.br |
| Endereço de e-Mail | abertachini@terra.com.br |
| Revista | Acta Astronautica |
| Volume | 63 |
| Número | 11-12 |
| Páginas | 1221-1232 |
| Nota Secundária | B_ENGENHARIAS_I B_ENGENHARIAS_II B_ENGENHARIAS_III B_ENGENHARIAS_IV C_GEOCIÊNCIAS C_INTERDISCIPLINAR |
| Histórico (UTC) | 2008-12-04 16:12:41 :: lattes -> simone :: 2010-07-07 18:38:51 :: simone -> marciana :: 2013-02-06 15:59:18 :: marciana -> administrator :: 2008 2021-02-11 18:11:17 :: administrator -> marciana :: 2008 |
| 3. Conteúdo e estrutura | |
| É a matriz ou uma cópia? | é a matriz |
| Estágio do Conteúdo | concluido |
| Transferível | 1 |
| Tipo do Conteúdo | External Contribution |
| Tipo de Versão | publisher |
| Palavras-Chave | Astrodinamica |
| Resumo | he well-known Lagrangian points that appear in the planar restricted three-body problem are very important for astronautical applications. They are five points of equilibrium in the equations of motion, what means that a particle located at one of those points with zero velocity will remain there indefinitely. The collinear points (L-1, L-2 and L-3) are always unstable and the triangular points (L-4 and L-5) are stable in the present case studied (Earth-Sun system). They are all very good points to locate a space-station, since they require a small amount of AV (and fuel), the control to be used, for station-keeping. The triangular points are especially good for this purpose, since they are stable equilibrium points. In this paper, the planar restricted four-body problem applied to the Sun-Earth-Moon-Spacecraft is combined with numerical integration and gradient methods to solve the two-point boundary value problem. This combination is applied to the search of families of transfer orbits between the Lagrangian points and the Earth, in the Earth-Sun system, with the minimum possible cost of the control used. So, the final goal of this paper is to find the magnitude of the two impulses to be applied in the spacecraft to complete the transfer: the first one when leaving/arriving at the Lagrangian point and the second one when arriving/living at the Earth. The dynamics given by the restricted four-body problem is used to obtain the trajectory of the spacecraft, but not the position of the equilibrium points. Their position is taken from the restricted three-body model. The goal to use this model is to evaluate the perturbation of the Sun in those important trajectories, in terms of fuel consumption and time of flight. The solutions will also show how to apply the impulses to accomplish the transfers under this force model. The results showed a large collection of transfers, and that there are initial conditions (position of the Sun with respect to the other bodies) where the force of the Sun can be used to reduce the cost of the transfers. |
| Área | ETES |
| Arranjo | urlib.net > BDMCI > Fonds > Produção anterior à 2021 > DIDMC > Transfer orbits to/from... |
| Conteúdo da Pasta doc | acessar |
| Conteúdo da Pasta source | não têm arquivos |
| Conteúdo da Pasta agreement | não têm arquivos |
| 4. Condições de acesso e uso | |
| Idioma | en |
| Grupo de Usuários | lattes marciana |
| Visibilidade | shown |
| Política de Arquivamento | denypublisher denyfinaldraft24 |
| Permissão de Leitura | deny from all and allow from 150.163 |
| Permissão de Atualização | não transferida |
| 5. Fontes relacionadas | |
| Unidades Imediatamente Superiores | 8JMKD3MGPCW/446AF4B |
| Divulgação | WEBSCI; PORTALCAPES; COMPENDEX. |
| Acervo Hospedeiro | dpi.inpe.br/plutao@80/2008/08.19.15.01 |
| 6. Notas | |
| Campos Vazios | alternatejournal archivist callnumber copyholder copyright creatorhistory descriptionlevel format isbn lineage mark mirrorrepository month nextedition notes orcid parameterlist parentrepositories previousedition previouslowerunit progress project readergroup resumeid rightsholder schedulinginformation secondarydate secondarykey session shorttitle sponsor subject targetfile tertiarymark tertiarytype typeofwork url |
| 7. Controle da descrição | |
| e-Mail (login) | marciana |
| atualizar | |