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1. Identity statement
Reference TypeThesis or Dissertation (Thesis)
Sitemtc-m16b.sid.inpe.br
Holder Codeisadg {BR SPINPE} ibi 8JMKD3MGPCW/3DT298S
Identifier6qtX3pFwXQZ3P8SECKy/GL24r
Repositorysid.inpe.br/jeferson/2005/07.14.18.30
Last Update2020:02.14.14.30.17 (UTC) sergio
Metadata Repositorysid.inpe.br/jeferson/2005/07.14.18.30.23
Metadata Last Update2024:12.26.14.49.42 (UTC) administrator
Secondary KeyINPE-12539-TDI/1001
Citation KeyFelipe:2004:TrOrEn
TitleTransferência orbitais envolvendo órbitas do tipo halo
Alternate TitleTransfers involving orbits of type halo
CourseCMC-SPG-INPE-MCT-BR
Year2004
Secondary Date2005-06-07
Date2004-03-19
Access Date2024, Dec. 26
Thesis TypeTese (Doutorado em Mecânica Espacial e Controle)
Secondary TypeTDI
Number of Pages222
Number of Files1
Size3601 KiB
2. Context
AuthorFelipe, Gislaine de
GroupSPG-INPE-MCT-BR
CommitteeMoraes, Rodolpho Vilhena de (presidente)
Prado, Antonio Fernando Bertachini de Almeida (orientador)
Winter, Othon Cabo
Chiaradia, Ana Paula Martins
Zanardi, Maria Cecília França de Paula Santos
UniversityInstituto Nacional de Pesquisas Espaciais (INPE)
CitySão José dos Campos
History (UTC)2005-07-14 18:31:57 :: jefferson -> jeferson ::
2005-09-20 14:29:18 :: jeferson -> jefferson ::
2007-09-05 17:05:34 :: jefferson -> administrator ::
2008-08-21 20:44:41 :: administrator -> jefferson ::
2008-11-11 17:04:27 :: jefferson -> administrator ::
2009-07-07 20:05:37 :: administrator -> jefferson ::
2012-07-18 14:58:44 :: jefferson -> ivone@sid.inpe.br ::
2012-07-18 14:59:41 :: ivone@sid.inpe.br -> administrator :: 2004
2012-10-21 21:44:29 :: administrator -> ivone@sid.inpe.br :: 2004
2013-01-14 19:46:51 :: ivone@sid.inpe.br -> administrator :: 2004
2018-06-05 03:52:25 :: administrator -> tereza@sid.inpe.br :: 2004
2019-04-01 14:32:14 :: tereza@sid.inpe.br -> simone :: 2004
2020-02-14 14:29:26 :: simone -> sergio :: 2004
2020-02-14 14:31:52 :: sergio -> administrator :: 2004
2024-12-26 14:49:42 :: administrator -> sergio :: 2004
3. Content and structure
Is the master or a copy?is the master
Content Stagecompleted
Transferable1
Keywordstransferência de órbitas
órbita de Rendezvous
mecânica orbital
manobra orbital
problemas de três corpos
órbitas de veículos espaciais
transfer orbits
orbital Rendezvous
orbital mechanics
orbital maneuvers
three body problems
spacecraf orbits
AbstractNas atividades espaciais, é de grande importância o estudo das trajetórias que os veículos espaciais devem seguir para completar uma missão. No presente trabalho, estudam-se as manobras orbitais envolvendo órbitas Halo para vários sistemas de primários. Para realizar este estudo utiliza-se o método de Lindstedt-Poincaré para a determinação das órbitas e o método de Lambert para as transferências envolvidas, tanto para as transferências com tempo livre como para as manobras de rendez-vous. Para exemplificar as técnicas desenvolvidas uma missão completa no sistema Terra-Lua envolvendo o problema restrito de três corpos é calculada em detalhes. Ainda estudam-se neste trabalho as mesmas manobras para o problema restrito bi-circular de quatro corpos. A seguir, um modelo propulsado de swing-by é desenvolvido e a sua eficiência em transferir um veiculo entre uma órbita de estacionamento em tomo da Terra até uma órbita Halo no sistema Terra-Sol utilizando um swing-by coma Lua é medida. ABSTRACT: In space activities, it is of great importance the study of trajectories that the space vehicles should follow to complete a mission. In the present work, maneuvers involving Halo orbits for several systems of primary are studied. To accomplish this study the method of Lindstedt-Poincaré is used for the etermination of the orbits and the method of Lambert is used for the transfers involved in both cases for the transfers with free time for the rendez-vous maneuvers. To exemplify the techniques developed here a complete mission in the Earth-Moon system involving the restricted three bodies problem is calculated in details. It is still studied in this work the same maneuvers for the restricted bi-circular problem of four bodies. To proceed, a propelled model for the swing-by is studied and its efficiency in transfering a spacecraft from a parking orbit around the Earth to a Halo orbit in the Earth-Sun system using a swing-by with the Moon is measured.
AreaETES
Arrangementurlib.net > BDMCI > Fonds > Produção pgr ATUAIS > CMC > Transferência orbitais envolvendo...
doc Directory Contentaccess
source Directory Content
publicacao.pdf 14/02/2020 11:31 3.5 MiB
agreement Directory Content
TERMO DE DEPOSITO ASSINADO GISLAINE DE FELIPE DOUTORADO.pdf 14/02/2020 11:30 407.3 KiB 
4. Conditions of access and use
data URLhttp://urlib.net/ibi/6qtX3pFwXQZ3P8SECKy/GL24r
zipped data URLhttp://urlib.net/zip/6qtX3pFwXQZ3P8SECKy/GL24r
Languagept
Target Filepublicacao.pdf
User Groupadministrator
ivone@sid.inpe.br
jefferson
sergio
simone
Visibilityshown
Copyright Licenseurlib.net/www/2012/11.12.15.10
Copy HolderSID/SCD
Read Permissionallow from all
Update Permissionnot transferred
5. Allied materials
Next Higher Units8JMKD2USNNW34T/4CL6N3H
8JMKD3MGPCW/3F2UALS
Citing Item Listsid.inpe.br/bibdigital/2013/10.14.00.13 11
DisseminationNTRSNASA; BNDEPOSITOLEGAL.
Host Collectioncptec.inpe.br/walmeida/2003/04.25.17.12
6. Notes
Empty Fieldsacademicdepartment affiliation archivingpolicy archivist callnumber contenttype creatorhistory descriptionlevel doi e-mailaddress electronicmailaddress format isbn issn label lineage mark mirrorrepository nextedition notes number orcid parameterlist parentrepositories previousedition previouslowerunit progress readergroup resumeid rightsholder schedulinginformation secondarymark session shorttitle sponsor subject tertiarymark tertiarytype url versiontype
7. Description control
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