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1. Identity statement
Reference TypeJournal Article
Sitemtc-m16b.sid.inpe.br
Holder Codeisadg {BR SPINPE} ibi 8JMKD3MGPCW/3DT298S
Identifier6qtX3pFwXQZGivnK2Y/SiHdi
Repositorysid.inpe.br/mtc-m17@80/2007/11.29.19.16   (restricted access)
Last Update2007:11.29.19.19.59 (UTC) marciana
Metadata Repositorysid.inpe.br/mtc-m17@80/2007/11.29.19.16.04
Metadata Last Update2021:02.11.18.12.07 (UTC) administrator
Secondary KeyINPE--PRE/
DOI10.1155/2007/49781
ISSN1024-123X
1563-5147
Citation KeyMoraesSilvKuga:2007:SiOrDe
TitleSimple Orbit Determination Using GPS Based on a Least-Squares Algorithm Employing Sequential Givens Rotations
Year2007
Access Date2024, May 18
Secondary TypePRE PI
Number of Files1
Size377 KiB
2. Context
Author1 Moraes, Rodolpho Vilhena de
2 Silva, Aurea Aparecida da
3 Kuga, Helio Koiti
Resume Identifier1
2
3 8JMKD3MGP5W/3C9JHC9
Group1
2 DMC-INPE-MCT-BR
3 DMC-INPE-MCT-BR
Affiliation1 Departamento de Matemática, UNESP Campus de Guaratinguetá, Guaratinguetá 12516-410, SP, Brazil
2 Instituto Nacional de Pesquisas Espaciais (INPE)
3 Instituto Nacional de Pesquisas Espaciais (INPE)
JournalMathematical Problems in Engineering
VolumeArticle ID 49781
History (UTC)2007-11-29 19:19:59 :: marciana -> administrator ::
2010-05-11 02:12:02 :: administrator -> marciana ::
2011-05-29 09:55:55 :: marciana -> administrator :: 2007
2014-08-19 19:20:48 :: administrator -> marciana :: 2007
2014-08-19 19:21:24 :: marciana -> administrator :: 2007
2021-02-11 18:12:07 :: administrator -> marciana :: 2007
3. Content and structure
Is the master or a copy?is the master
Content Stagecompleted
Transferable1
Content TypeExternal Contribution
Version Typepublisher
AbstractA low-cost computer procedure to determine the orbit of an artificial satellite by using short arc data from an onboard GPS receiver is proposed. Pseudoranges are used as measurements to estimate the orbit via recursive least squares method. The algorithm applies orthogonal Givens rotations for solving recursive and sequential orbit determination problems. To assess the procedure, it was applied to the TOPEX/POSEIDON satellite for data batches of one orbital period (approximately two hours), and force modelling, due to the full JGM-2 gravity field model, was considered. When compared with the reference Precision Orbit Ephemeris (POE) of JPL/NASA, the results have indicated that precision better than 9 m is easily obtained, even when short batches of data are used.
AreaETES
Arrangementurlib.net > BDMCI > Fonds > Produção anterior à 2021 > DIDMC > Simple Orbit Determination...
doc Directory Contentaccess
source Directory Contentthere are no files
agreement Directory Contentthere are no files
4. Conditions of access and use
Languageen
Target FilemoraesS1024123X07497812[1].pdf
User Groupadministrator
marciana
Reader Groupadministrator
marciana
Visibilityshown
Archiving Policydenypublisher allowfinaldraft
Read Permissiondeny from all and allow from 150.163
Update Permissionnot transferred
5. Allied materials
Next Higher Units8JMKD3MGPCW/446AF4B
Citing Item Listsid.inpe.br/mtc-m21/2012/07.13.14.49.46 1
DisseminationWEBSCI; PORTALCAPES; COMPENDEX.
Host Collectionlcp.inpe.br/ignes/2004/02.12.18.39
cptec.inpe.br/walmeida/2003/04.25.17.12
6. Notes
Empty Fieldsalternatejournal archivist callnumber copyholder copyright creatorhistory descriptionlevel e-mailaddress electronicmailaddress format isbn keywords label lineage mark mirrorrepository month nextedition notes number orcid pages parameterlist parentrepositories previousedition previouslowerunit progress project rightsholder schedulinginformation secondarydate secondarymark session shorttitle sponsor subject tertiarymark tertiarytype typeofwork url
7. Description control
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