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1. Identity statement
Reference TypeJournal Article
Siteplutao.sid.inpe.br
Holder Codeisadg {BR SPINPE} ibi 8JMKD3MGPCW/3DT298S
Identifier8JMKD3MGP3W/3KN2N3N
Repositorysid.inpe.br/plutao/2015/12.04.12.02.35   (restricted access)
Last Update2015:12.11.12.58.19 (UTC) administrator
Metadata Repositorysid.inpe.br/plutao/2015/12.04.12.02.36
Metadata Last Update2021:07.28.22.22.43 (UTC) administrator
DOI10.1088/1742-6596/641/1/012002
ISSN1742-6588
Labellattes: 7340081273816424 3 FerreiraKugaPradWint:2015:EsTrSp
Citation KeyFerreiraKugaPradWint:2015:EsTrSp
TitleEstimating the trajectory of a space vehicle passing by the Moon using Kalman Filter
Year2015
Access Date2024, May 25
Secondary TypePRE PI
Number of Files1
Size912 KiB
2. Context
Author1 Ferreira, A. Ferraz Silva
2 Kuga, Hélio Koiti
3 Prado, Antonio Fernando Bertachini de Almeida
4 Winter, O. C.
Resume Identifier1
2 8JMKD3MGP5W/3C9JHC9
3 8JMKD3MGP5W/3C9JGJA
Group1
2 DMC-ETE-INPE-MCTI-GOV-BR
3 DMC-ETE-INPE-MCTI-GOV-BR
Affiliation1
2 Instituto Nacional de Pesquisas Espaciais (INPE)
3 Instituto Nacional de Pesquisas Espaciais (INPE)
4 Universidade Estadual Paulista (UNESP)
Author e-Mail Address1 aleferrazsilva@hotmail.com
2 helio.kuga@inpe.br
3 antonio.prado@inpe.br
JournalJournal of Physics: Conference Series
Volume641
Pages012002
Secondary MarkB2_INTERDISCIPLINAR B2_ENGENHARIAS_III B3_MEDICINA_II B3_GEOCIÊNCIAS B4_MATERIAIS B4_ENGENHARIAS_II B4_BIOTECNOLOGIA C_QUÍMICA C_MATEMÁTICA_/_PROBABILIDADE_E_ESTATÍSTICA C_ENGENHARIAS_IV C_ECONOMIA C_ASTRONOMIA_/_FÍSICA
History (UTC)2015-12-04 12:02:36 :: lattes -> administrator ::
2021-07-28 22:22:43 :: administrator -> simone :: 2015
3. Content and structure
Is the master or a copy?is the master
Content Stagecompleted
Transferable1
Content TypeExternal Contribution
Version Typepublisher
KeywordsAstrodinâmica
AbstractThe trajectory of a spacecraft going to the periapsis of its orbit around the smaller body of a binary system is estimated from the observed data using a Kalman Filter. Simulations of the trajectories will be made to generate the data of the spacecraft position. When observed from the Earth, using a fixed star as a reference, we have the spacecraft position as an angle function ϕ. This is the angle between spacecraft position vector and the star position vector. The result shows that Kalman Filter can be used successfully for trajectory estimation, if adequate accuracy is available for the angle observations.
AreaETES
Arrangementurlib.net > BDMCI > Fonds > Produção anterior à 2021 > DIDMC > Estimating the trajectory...
doc Directory Contentaccess
source Directory Contentthere are no files
agreement Directory Contentthere are no files
4. Conditions of access and use
Languagept
Target File1_ferreira3.pdf
User Grouplattes
simone
Reader Groupadministrator
simone
Visibilityshown
Archiving Policydenypublisher denyfinaldraft12
Read Permissiondeny from all and allow from 150.163
Update Permissionnot transferred
5. Allied materials
Mirror Repositoryurlib.net/www/2011/03.29.20.55
Next Higher Units8JMKD3MGPCW/446AF4B
Citing Item Listsid.inpe.br/bibdigital/2021/02.11.18.06 3
DisseminationWEBSCI; PORTALCAPES; COMPENDEX; SCOPUS.
Host Collectiondpi.inpe.br/plutao@80/2008/08.19.15.01
6. Notes
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