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1. Identity statement
Reference TypeBook Section
Sitemtc-m16.sid.inpe.br
Holder Codeisadg {BR SPINPE} ibi 8JMKD3MGPCW/3DT298S
Identifier8JMKD3MGPDW/3CBMCH2
Repositorysid.inpe.br/mtc-m16/2012/07.26.13.30
Last Update2012:07.26.13.34.53 (UTC) administrator
Metadata Repositorysid.inpe.br/mtc-m16/2012/07.26.13.30.18
Metadata Last Update2018:06.05.01.28.54 (UTC) administrator
ISBN85-901487-1-8
Citation KeyFelipePrad:1998:OpMaTh
TitleOptimal maneuvers in three-dimensional swing-by trajectories
ProjectDinâmica orbital
Year1998
Access Date2025, July 02
Secondary TypePRE LI
Number of Files1
Size367 KiB
2. Context
Author1 Felipe, Gislaine
2 Prado, Antonio Fernando Bertachini de Almeida
Group1 INPE-MCT-BR
Affiliation1 Instituto Nacional de Pesquisas Espaciais (INPE)
2 University of Texas at Austin
Author e-Mail Address1 prado@dem.inpe.br
EditorPrado, Antonio Fernando Bertachini de Almeida
e-Mail Addresswschulz@iae.cta.br
Book TitleAdvances in space dynamics
PublisherINPE
CitySão José dos Campos
Pages63-83
History (UTC)2012-08-01 16:54:38 :: prado@dem.inpe.br -> administrator :: 1998
2018-06-05 01:28:54 :: administrator -> prado@dem.inpe.br :: 1998
3. Content and structure
Is the master or a copy?is the master
Content Stagecompleted
Transferable1
Keywordsastrodynamics
orbital maneuvers
swing-vy
close approaches
AbstractThe swing-by maneuver uses a close approach with a celestial body to modify the velocity, energy and angular momentum of a spacecraft. The literature has several papers studying this problem, usually using a patched-conic approximation. In the present paper the swing-by maneuvers are studied and classified under the model given by the three-dimensional restricted three-body problem. To show the results, the orbits of the spacecraft are classified in four groups: elliptic direct, elliptic retrograde, hyperbolic direct and hyperbolic retrograde. Then, the modification in the orbit of the spacecraft due to the close approach is shown in plots that specify from which group of orbits the spacecraft is coming and to which group it is going. The results generated here are used to solve optimal problems, such as finding trajectories that satisfy some given constraints (such as achieving an escape or a capture) with some parameters being extremized (position, velocity, etc...). Three optimal problems are solved in this paper to show this application.
AreaETES
doc Directory Contentaccess
source Directory Contentthere are no files
agreement Directory Content
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4. Conditions of access and use
data URLhttp://urlib.net/ibi/8JMKD3MGPDW/3CBMCH2
zipped data URLhttp://urlib.net/zip/8JMKD3MGPDW/3CBMCH2
Languageen
Target FileOptimalSB3D.pdf
User Groupadministrator
jefferson
prado@dem.inpe.br
Visibilityshown
Copy HolderSID/SCD
5. Allied materials
DisseminationNTRSNASA; BNDEPOSITOLEGAL.
Host Collectionsid.inpe.br/banon/2003/08.15.17.40
6. Notes
Empty Fieldsarchivingpolicy archivist callnumber contenttype copyright creatorhistory descriptionlevel documentstage doi edition format issn label lineage mark mirrorrepository nextedition nexthigherunit notes numberofvolumes orcid parameterlist parentrepositories previousedition previouslowerunit progress readergroup readpermission resumeid rightsholder schedulinginformation secondarydate secondarykey secondarymark serieseditor seriestitle session shorttitle sponsor subject tertiarymark tertiarytype translator url versiontype volume
7. Description control
e-Mail (login)prado@dem.inpe.br
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