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1. Identity statement
Reference TypeJournal Article
Sitemtc-m16b.sid.inpe.br
Holder Codeisadg {BR SPINPE} ibi 8JMKD3MGPCW/3DT298S
Identifier6qtX3pFwXQZGivnK2Y/Shwqd
Repositorysid.inpe.br/mtc-m17@80/2007/11.27.17.30.15   (restricted access)
Last Update2007:11.27.17.46.35 (UTC) administrator
Metadata Repositorysid.inpe.br/mtc-m17@80/2007/11.27.17.30.16
Metadata Last Update2021:02.11.18.12.05 (UTC) administrator
Secondary KeyINPE--PRE/
DOI10.1016/j.asr.2007.04.098
ISSN0273-1177
Citation KeyPradoFeli:2007:AnStPo
TitleAn analytical study of the powered swing-by to perform orbital maneuvers
Year2007
Access Date2024, Apr. 28
Secondary TypePRE PI
Number of Files1
Size591 KiB
2. Context
Author1 Prado, Antonio Fernando Bertachini de Almeida
2 Felipe, Gislaine de
Resume Identifier1 8JMKD3MGP5W/3C9JGJA
Group1 DMC-INPE-MCT-BR
2 DMC-INPE-MCT-BR
Affiliation1 Instituto Nacional de Pesquisas Espaciais (INPE)
2 Instituto Nacional de Pesquisas Espaciais (INPE)
JournalAdvances in Space Research
Volume40
Number12
Pages1769-1968
History (UTC)2007-11-27 18:03:27 :: marciana -> administrator ::
2010-05-11 02:11:49 :: administrator -> marciana ::
2011-05-20 22:30:43 :: 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
Swing-by
Orbital maneuvers
Patched-conics approximation
AbstractIn the present paper, we present an analytical description of the powered swing-by maneuver in the three-dimensional space. To perform this task, new analytical equations are derived for the three-dimensional unpowered swing-by, including the variation in velocity, angular momentum, energy and inclination of the spacecraft due to the maneuver. This is done based on the patched-conics approximation. From those general three-dimensional equations, it is possible to confirm some well-known analytical results for the planar case. The equations developed here are verified by numerical integrations, using the restricted problem of three bodies, showing an agreement better than 1%. After that, based on those equations, some new analytical results are obtained for the situation when an impulse is applied to the spacecraft during the close approach. Those new equations are based in the assumption that the impulse applied is small compared to the velocity of the spacecraft, and they allow the calculation of the same variations cited above. Those equations can be simplified for specific cases, and it can generate some conclusions about the direction to apply the impulse to attend specific goals. A study is also executed to investigate in which cases the impulse is more efficient when applied at the periapsis of the swing-by hyperbola or at points far way from the swing-by body.
AreaETES
Arrangementurlib.net > BDMCI > Fonds > Produção anterior à 2021 > DIDMC > An analytical study...
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4. Conditions of access and use
Languageen
Target Fileprado3.pdf
User Groupadministrator
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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7. Description control
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