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1. Identity statement
Reference TypeJournal Article
Siteplutao.sid.inpe.br
Holder Codeisadg {BR SPINPE} ibi 8JMKD3MGPCW/3DT298S
IdentifierJ8LNKAN8RW/3D537AA
Repositorydpi.inpe.br/plutao/2012/11.28.14.05.41   (restricted access)
Last Update2012:11.29.13.02.23 (UTC) administrator
Metadata Repositorydpi.inpe.br/plutao/2012/11.28.14.05.42
Metadata Last Update2021:02.11.18.11.15 (UTC) administrator
Secondary KeyINPE--PRE/
DOI10.1016/j.asr.2012.07.028
ISSN0273-1177
Labellattes: 7340081273816424 2 SukhanovPrad:2012:OnApOp
Citation KeySukhanovPrad:2012:OnApOp
TitleOn one approach to the optimization of low-thrust station keeping manoeuvres
Year2012
MonthDec.
Access Date2024, Mar. 28
Secondary TypePRE PI
Number of Files1
Size707 KiB
2. Context
Author1 Sukhanov, A. A.
2 Prado, Antonio Fernando Bertachini de Almeida
Resume Identifier1
2 8JMKD3MGP5W/3C9JGJA
Group1
2 DMC-ETE-INPE-MCTI-GOV-BR
Affiliation1 Space Research Institute (IKI) of the Russian Academy of Sciences, 117997, 84/32 Profsoyuznaya Str, Moscow, Russia
2 Instituto Nacional de Pesquisas Espaciais (INPE)
Author e-Mail Address1
2 prado@dem.inpe.br
e-Mail Addressprado@dem.inpe.br
JournalAdvances in Space Research
Volume50
Number11
Pages1478-1488
Secondary MarkB4_ASTRONOMIA_/_FÍSICA B3_CIÊNCIAS_BIOLÓGICAS_I B1_ENGENHARIAS_III B1_ENGENHARIAS_IV B1_GEOCIÊNCIAS B1_INTERDISCIPLINAR
History (UTC)2012-11-28 23:06:21 :: lattes -> administrator :: 2012
2012-11-29 12:50:33 :: administrator -> marciana :: 2012
2012-11-29 13:02:23 :: marciana -> administrator :: 2012
2013-02-05 21:02:32 :: administrator -> banon :: 2012
2013-02-18 14:43:25 :: banon -> administrator :: 2012
2021-02-11 18:11:15 :: administrator -> marciana :: 2012
3. Content and structure
Is the master or a copy?is the master
Content Stagecompleted
Transferable1
Content TypeExternal Contribution
Version Typepublisher
KeywordsAstrodinâmica
Manobras Orbitais
Manobras Espaciais
AbstractA simple and effective mathematical method to calculate optimal station-keeping manoeuvres by means of electric propulsion is suggested. The method is based on a linearization of the satellite motion near a reference orbit. Two versions of the method allow station keeping both in an assigned position and in any position of the orbit. The method is fully analytical for the two-body problem and takes a simpler form for the circular assigned orbit. The suggested method may also be used in the case when constraints are imposed on the thrust direction due to specific features of the satellite stabilization mode. An application of the method to any force field is shown. Illustrative examples of satellite station keeping in a circular orbit are given. Both cases of the station keeping, i.e., in an assigned position and in an assigned orbit, are considered without and with a constraint on the thrust direction.
AreaETES
Arrangementurlib.net > BDMCI > Fonds > Produção anterior à 2021 > DIDMC > On one approach...
doc Directory Contentaccess
source Directory Contentthere are no files
agreement Directory Contentthere are no files
4. Conditions of access and use
Languageen
Target File1-s2.0-S0273117712005042-sukhanov.pdf
User Groupadministrator
banon
lattes
marciana
Visibilityshown
Archiving Policydenypublisher denyfinaldraft24
Read Permissiondeny from all and allow from 150.163
Update Permissionnot transferred
5. Allied materials
Next Higher Units8JMKD3MGPCW/446AF4B
DisseminationWEBSCI; PORTALCAPES; MGA; COMPENDEX.
Host Collectiondpi.inpe.br/plutao@80/2008/08.19.15.01
6. Notes
Empty Fieldsalternatejournal archivist callnumber copyholder copyright creatorhistory descriptionlevel format isbn lineage mark mirrorrepository nextedition notes orcid parameterlist parentrepositories previousedition previouslowerunit progress project readergroup rightsholder schedulinginformation secondarydate session shorttitle sponsor subject tertiarymark tertiarytype typeofwork url
7. Description control
e-Mail (login)marciana
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