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1. Identity statement
Reference TypeJournal Article
Sitemtc-m16b.sid.inpe.br
Holder Codeisadg {BR SPINPE} ibi 8JMKD3MGPCW/3DT298S
Identifier6qtX3pFwXQZGivnK2Y/ShwPE
Repositorysid.inpe.br/mtc-m17@80/2007/11.27.17.51   (restricted access)
Last Update2007:11.27.17.54.54 (UTC) administrator
Metadata Repositorysid.inpe.br/mtc-m17@80/2007/11.27.17.51.20
Metadata Last Update2021:02.11.18.12.05 (UTC) administrator
Secondary KeyINPE--PRE/
DOI10.1016/j.asr.2007.01.012
ISSN0273-1177
Citation KeyPrado:2007:Co‘‘Ap
TitleA comparison of the ‘‘patched-conics approach’’ and the restricted problem for swing-bys
Year2007
Access Date2024, Apr. 28
Secondary TypePRE PI
Number of Files1
Size177 KiB
2. Context
AuthorPrado, Antonio Fernando Bertachini de Almeida
Resume Identifier8JMKD3MGP5W/3C9JGJA
GroupDMC-INPE-MCT-BR
AffiliationInstituto Nacional de Pesquisas Espaciais (INPE)
JournalAdvances in Space Research
Volume40
Number1
Pages113-117
History (UTC)2007-11-27 18:02:49 :: marciana -> administrator ::
2021-02-11 18:12:05 :: administrator -> marciana :: 2007
3. Content and structure
Is the master or a copy?is the master
Content Stagecompleted
Transferable1
Content TypeExternal Contribution
KeywordsAstrodynamics
Restricted problem
Swing-by
Space trajectories
Jupiter
AbstractIn the present paper we study swing-by maneuvers that use the planet Jupiter as the body for the close approach. The main goal is to simulate a large variety of initial conditions for those orbits and study the effects caused by the close approach with Jupiter in the orbit of the spacecraft. The planar restricted circular three-body problem and the patched-conics approach are used as the mathematical models. For the planar restricted circular three-body problem, the equations are regularized (using Lemaı tres regularization), so it is possible to avoid the numerical problems that come from the close approach with Jupiter. Then, the results obtained with these well-known dynamics are compared. We see that there is a good agreement of the two models studied in the majority of the situations, but there are large discrepancies in the results of the semi-major axis when the energy before or after the passage is small. There are differences in semi-major axis larger than 10% of the SunJupiter distance in about 5% of the trajectories simulated. Differences in the order of several hundreds of the SunJupiter distances were also encountered. 2007 COSPAR. Published by Elsevier Ltd. All rights reserved.
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4. Conditions of access and use
Languageen
Target Fileprado4.pdf
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marciana
Visibilityshown
Archiving Policydenypublisher denyfinaldraft24
Read Permissiondeny from all and allow from 150.163
5. Allied materials
Next Higher Units8JMKD3MGPCW/446AF4B
DisseminationWEBSCI; PORTALCAPES; MGA; COMPENDEX.
Host Collectionlcp.inpe.br/ignes/2004/02.12.18.39
cptec.inpe.br/walmeida/2003/04.25.17.12
6. Notes
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