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1. Identity statement
Reference TypeJournal Article
Siteplutao.sid.inpe.br
Holder Codeisadg {BR SPINPE} ibi 8JMKD3MGPCW/3DT298S
IdentifierJ8LNKAN8RW/38MQQSA
Repositorydpi.inpe.br/plutao/2010/12.02.13.23.50   (restricted access)
Last Update2011:01.04.13.23.09 (UTC) administrator
Metadata Repositorydpi.inpe.br/plutao/2010/12.02.13.23.51
Metadata Last Update2021:02.11.18.11.08 (UTC) administrator
Secondary KeyINPE--PRE/
DOI10.1007/s10569-010-9310-6
ISSN0923-2958
Labellattes: 7340081273816424 3 CarvalhoVilhPrad:2010:SoOrCh
Citation KeyCarvalhoVilhPrad:2010:SoOrCh
TitleSome orbital characteristics of lunar artificial satellites
Year2010
Access Date2024, May 21
Secondary TypePRE PI
Number of Files1
Size1008 KiB
2. Context
Author1 Carvalho, Jean P S
2 Vilhena de Moraes, R.
3 Prado, Antonio Fernando Bertachini de Almeida
Resume Identifier1
2
3 8JMKD3MGP5W/3C9JGJA
Group1
2
3 DMC-ETE-INPE-MCT-BR
Affiliation1 Univ Estadual Paulista, BR-12516410 Guaratingueta, SP Brazil
2 Univ Estadual Paulista, BR-12516410 Guaratingueta, SP Brazil
3 Instituto Nacional de Pesquisas Espaciais (INPE)
Author e-Mail Address1
2
3 abertachini@terra.com.br
e-Mail Addressabertachini@terra.com.br
JournalCelestial Mechanics and Dynamical Astronomy
Volume108
Pages371-388
Secondary MarkB4_ASTRONOMIA_/_FÍSICA A1_ENGENHARIAS_III B1_INTERDISCIPLINAR
History (UTC)2010-12-06 14:15:28 :: lattes -> ricardo :: 2010
2010-12-07 11:40:42 :: ricardo -> marciana :: 2010
2011-01-04 13:23:09 :: marciana -> administrator :: 2010
2012-07-25 15:49:21 :: administrator -> banon :: 2010
2012-09-24 17:15:47 :: banon -> administrator :: 2010
2021-02-11 18:11:08 :: administrator -> marciana :: 2010
3. Content and structure
Is the master or a copy?is the master
Content Stagecompleted
Transferable1
Content TypeExternal Contribution
KeywordsMAIN PROBLEM
3RD-BODY PERTURBATION
CRITICAL INCLINATION
FROZEN ORBITS
POLAR
MODEL
BODY
AbstractIn this paper we present an analytical theory with numerical simulations to study the orbital motion of lunar artificial satellites. We consider the problem of an artificial satellite perturbed by the non-uniform distribution of mass of the Moon and by a third-body in elliptical orbit (Earth is considered). Legendre polynomials are expanded in powers of the eccentricity up to the degree four and are used for the disturbing potential due to the third-body. We show a new approximated equation to compute the critical semi-major axis for the orbit of the satellite. Lie-Hori perturbation method up to the second-order is applied to eliminate the terms of short-period of the disturbing potential. Coupling terms are analyzed. Emphasis is given to the case of frozen orbits and critical inclination. Numerical simulations for hypothetical lunar artificial satellites are performed, considering that the perturbations are acting together or one at a time.
AreaETES
Arrangementurlib.net > BDMCI > Fonds > Produção anterior à 2021 > DIDMC > Some orbital characteristics...
doc Directory Contentaccess
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4. Conditions of access and use
Languageen
Target Fileprado.pdf
User Groupadministrator
banon
lattes
marciana
Visibilityshown
Archiving Policydenypublisher denyfinaldraft12
Read Permissiondeny from all and allow from 150.163
5. Allied materials
Next Higher Units8JMKD3MGPCW/446AF4B
DisseminationWEBSCI
Host Collectiondpi.inpe.br/plutao@80/2008/08.19.15.01
6. Notes
Empty Fieldsalternatejournal archivist callnumber copyholder copyright creatorhistory descriptionlevel documentstage format isbn lineage mark mirrorrepository month nextedition notes number orcid parameterlist parentrepositories previousedition previouslowerunit progress project readergroup rightsholder schedulinginformation secondarydate session shorttitle sponsor subject tertiarymark tertiarytype typeofwork url versiontype
7. Description control
e-Mail (login)marciana
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