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1. Identity statement
Reference TypeConference Paper (Conference Proceedings)
Sitemtc-m21b.sid.inpe.br
Holder Codeisadg {BR SPINPE} ibi 8JMKD3MGPCW/3DT298S
Identifier8JMKD3MGP3W34P/3KH6J52
Repositorysid.inpe.br/mtc-m21b/2015/11.04.15.00
Last Update2015:11.04.15.01.30 (UTC) administrator
Metadata Repositorysid.inpe.br/mtc-m21b/2015/11.04.15.00.52
Metadata Last Update2021:02.11.18.19.55 (UTC) administrator
Secondary KeyINPE--PRE/
Citation KeyGonçalvesRoccMora:2015:OrMaLu
TitleOrbital maneuvers of a lunar artificial satellite, under the action of gravitational and non-gravitational perturbation forces
Year2015
Access Date2024, May 14
Secondary TypePRE CI
Number of Files1
Size323 KiB
2. Context
Author1 Gonçalves, Liana Dias
2 Rocco, Evandro Marconi
3 Moraes, Rodolpho Vilhena de
Resume Identifier1
2 8JMKD3MGP5W/3C9JH37
Group1 CMC-ETES-SPG-INPE-MCTI-GOV-BR
2 DMC-ETE-INPE-MCTI-GOV-BR
Affiliation1 Instituto Nacional de Pesquisas Espaciais (INPE)
2 Instituto Nacional de Pesquisas Espaciais (INPE)
3 Universidade Federal de São Paulo (UNIFESP)
Author e-Mail Address1 lianadgon@gmail.com
2 evandro.rocco@inpe.br
3 rodolpho.vilhena@gmail.com
Conference NameInternational Symposium on Space Flight Dynamics, 25
Conference LocationMunich, Germany
Date19-23 Oct.
Book TitleProceedings
History (UTC)2015-11-04 15:00:52 :: simone -> administrator ::
2021-02-11 18:19:55 :: administrator -> simone :: 2015
3. Content and structure
Is the master or a copy?is the master
Content Stagecompleted
Transferable1
Content TypeExternal Contribution
Version Typefinaldraft
KeywordsAstrodynamics
Orbital Maneuvers
Continuous Thrust
Perturbations
AbstractThe objective of this study is to analyze the orbital maneuvers of an artificial satellite around the Moon surface subject to perturbative forces of gravitational and not gravitational origin, such as lunar gravitational potential, gravitational attraction of the Earth and the Sun, lunar albedo and solar radiation pressure. Optimal maneuvers were obtained from the Lambert's problem solution (Two Point Boundary Value Problem) in order that is minimized the fuel consumption. Then a selected maneuver was simulated assuming a more realistic model of the propulsion system. For both cases is analyzed the actions of thrusters, fuel consumption and deviations in the orbital elements that characterize the lunar orbit of artificial satellite. The deviation is obtained by a comparison between the actual state and the reference state of the vehicle at each step of the simulation. The actual state is calculated every step of the simulation and the reference state is determined considering the desired final orbital elements for the trajectory.
AreaETES
Arrangement 1urlib.net > BDMCI > Fonds > Produção pgr ATUAIS > CMC > Orbital maneuvers of...
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4. Conditions of access and use
data URLhttp://mtc-m21b.sid.inpe.br/ibi/8JMKD3MGP3W34P/3KH6J52
zipped data URLhttp://mtc-m21b.sid.inpe.br/zip/8JMKD3MGP3W34P/3KH6J52
User Groupsimone
Reader Groupadministrator
simone
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Read Permissionallow from all
Update Permissionnot transferred
5. Allied materials
Mirror Repositoryurlib.net/www/2011/03.29.20.55
Next Higher Units8JMKD3MGPCW/3F2UALS
8JMKD3MGPCW/446AF4B
Citing Item Listsid.inpe.br/mtc-m21/2012/07.13.14.45.41 6
Host Collectionsid.inpe.br/mtc-m21b/2013/09.26.14.25.20
6. Notes
Empty Fieldsarchivingpolicy archivist callnumber copyholder copyright creatorhistory descriptionlevel dissemination doi e-mailaddress edition editor format isbn issn label language lineage mark nextedition notes numberofvolumes orcid organization pages parameterlist parentrepositories previousedition previouslowerunit progress project publisher publisheraddress rightsholder schedulinginformation secondarydate secondarymark serieseditor session shorttitle sponsor subject targetfile tertiarymark tertiarytype type url volume
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