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1. Identificação
Tipo de ReferênciaArtigo em Evento (Conference Proceedings)
Sitemtc-m21b.sid.inpe.br
Código do Detentorisadg {BR SPINPE} ibi 8JMKD3MGPCW/3DT298S
Identificador8JMKD3MGP3W34P/3KH6HRB
Repositóriosid.inpe.br/mtc-m21b/2015/11.04.14.57
Última Atualização2015:11.04.14.57.53 (UTC) administrator
Repositório de Metadadossid.inpe.br/mtc-m21b/2015/11.04.14.57.33
Última Atualização dos Metadados2021:02.11.18.19.54 (UTC) administrator
Chave SecundáriaINPE--PRE/
Chave de CitaçãoRocco:2015:IOEuGa
TítuloManeuvers around jupiter with automatic correction of the trajectory considering gravitational disturbances generated by the Galilean moons: IO, Europa Ganymede and Callisto
Ano2015
Data de Acesso05 maio 2024
Tipo SecundárioPRE CI
Número de Arquivos1
Tamanho512 KiB
2. Contextualização
AutorRocco, Evandro Marconi
Identificador de Curriculo8JMKD3MGP5W/3C9JH37
GrupoDMC-ETE-INPE-MCTI-GOV-BR
AfiliaçãoInstituto Nacional de Pesquisas Espaciais (INPE)
Endereço de e-Mail do Autorevandro.rocco@inpe.br
Nome do EventoInternational Symposium on Space Flight Dynamics, 25
Localização do EventoMunich, Germany
Data19-23 Oct.
Título do LivroProceedings
Histórico (UTC)2015-11-04 14:57:33 :: simone -> administrator ::
2021-02-11 18:19:54 :: administrator -> simone :: 2015
3. Conteúdo e estrutura
É a matriz ou uma cópia?é a matriz
Estágio do Conteúdoconcluido
Transferível1
Tipo do ConteúdoExternal Contribution
Tipo de Versãofinaldraft
Palavras-ChaveAstrodynamics
Orbital Maneuvers
Continuous Thrust
Automatic Correction
ResumoThe goal of this study is to evaluate the influence of the gravitational attraction of the Sun, and the Galilean moons, during orbital maneuvers of a spacecraft orbiting Jupiter. Initially ideal thrusters, capable of applying infinite magnitude of the thrust, were used. Thus, impulsive optimal maneuvers were obtained by scanning the solutions of the Two Point Boundary Value Problem (TPBVP) for various values of transfer time in order to select the impulsive maneuver of minimum necessary velocity increment. Then, the selected maneuver was simulated considering a more realistic model of the propulsion system. In fact is not possible to accomplish an impulsive maneuver. Thus, the orbital maneuver must be distributed in a propulsive arc around the position of the impulse given by the solution of the TPBVP. In this arc was used a continuous thrust, limited to the capacity of the thrusters, with automatic correction of the trajectory. However the effect of the propulsive arc is not exactly equivalent to the application of an impulse. The evaluation of the difference between these approaches is extremely relevant in the mission analysis and spacecraft design of the trajectory control system. Therefore, the influence of the capacity of thrusters in the trajectory was evaluated for a more realistic model instead of the ideal case represented by the impulsive approach.
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4. Condições de acesso e uso
URL dos dadoshttp://urlib.net/ibi/8JMKD3MGP3W34P/3KH6HRB
URL dos dados zipadoshttp://urlib.net/zip/8JMKD3MGP3W34P/3KH6HRB
Idiomaen
Grupo de Usuáriossimone
Grupo de Leitoresadministrator
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Visibilidadeshown
Permissão de Leituraallow from all
Permissão de Atualizaçãonão transferida
5. Fontes relacionadas
Repositório Espelhourlib.net/www/2011/03.29.20.55
Unidades Imediatamente Superiores8JMKD3MGPCW/446AF4B
Lista de Itens Citandosid.inpe.br/mtc-m21/2012/07.13.14.45.41 3
sid.inpe.br/bibdigital@80/2006/04.07.15.50.13 1
Acervo Hospedeirosid.inpe.br/mtc-m21b/2013/09.26.14.25.20
6. Notas
Campos Vaziosarchivingpolicy archivist callnumber copyholder copyright creatorhistory descriptionlevel dissemination doi e-mailaddress edition editor format isbn issn label lineage mark nextedition notes numberofvolumes orcid organization pages parameterlist parentrepositories previousedition previouslowerunit progress project publisher publisheraddress rightsholder schedulinginformation secondarydate secondarymark serieseditor session shorttitle sponsor subject targetfile tertiarymark tertiarytype type url volume
7. Controle da descrição
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