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1. Identity statement
Reference TypeJournal Article
Sitemtc-m21b.sid.inpe.br
Holder Codeisadg {BR SPINPE} ibi 8JMKD3MGPCW/3DT298S
Identifier8JMKD3MGP5W34M/3FA7RES
Repositorysid.inpe.br/mtc-m21b/2013/11.27.13.22.18   (restricted access)
Last Update2015:03.11.13.07.17 (UTC) administrator
Metadata Repositorysid.inpe.br/mtc-m21b/2013/11.27.13.22.19
Metadata Last Update2021:02.11.18.12.15 (UTC) administrator
DOI10.1155/2013/234270
ISSN1024-123X
Labelisi 2013-11
Citation KeySantosKugaRocc:2013:ApKaFi
TitleApplication of the Kalman Filter to Estimate the State of an Aerobraking Maneuver
Year2013
Access Date2024, May 15
Type of Workjournal article
Secondary TypePRE PI
Number of Files1
Size4554 KiB
2. Context
Author1 Santos, Willer Gomes dos
2 Kuga, Helio Koiti
3 Rocco, Evandro Marconi
Resume Identifier1
2 8JMKD3MGP5W/3C9JHC9
3 8JMKD3MGP5W/3C9JH37
Group1 CMC-ETES-SPG-INPE-MCTI-GOV-BR
2 DMC-ETE-INPE-MCTI-GOV-BR
3 DMC-ETE-INPE-MCTI-GOV-BR
Affiliation1 Instituto Nacional de Pesquisas Espaciais (INPE)
2 Instituto Nacional de Pesquisas Espaciais (INPE)
3 Instituto Nacional de Pesquisas Espaciais (INPE)
Author e-Mail Address1 willer.gomes@dem.inpe.br
2 hkk@dem.inpe.br
3 evandro@dem.inpe.br
e-Mail Addressmarcelo.pazos@inpe.br
JournalMathematical Problems in Engineering
Volume2013
Secondary MarkB1 B1 B1 B1 B1 B2 B3 B3 B4 B4 B5
History (UTC)2021-02-11 18:12:15 :: administrator -> marcelo.pazos@inpe.br :: 2013
3. Content and structure
Is the master or a copy?is the master
Content Stagecompleted
Transferable1
Content TypeExternal Contribution
Version Typepublisher
Keywordsatmospheric model
estimation algorithm
external disturbances
pid controllers
propagation equations
reference trajectories
sensors and actuators
standard atmospheres
estimation
Kalman filters
sensors
spacecraft
aerobraking
AbstractThis paper presents a study about the application of a Kalman filter to estimate the position and velocity of a spacecraft in an aerobraking maneuver around the Earth. The cis-lunar aerobraking of the Hiten spacecraft as well as an aerobraking in a LEO orbit are simulated in this paper. The simulator developed considers a reference trajectory and a trajectory perturbed by external disturbances combined with nonidealities of sensors and actuators. It is able to operate in closed loop controlling the trajectory at each instant of time using a PID controller and propulsive jets. A Kalman filter utilizes the sensor data to estimate the state of the spacecraft. The estimation algorithms and propagation equations used in this process are presented. The U.S. Standard Atmosphere is adopted as the atmospheric model. The main results are compared with the case where the Kalman filter is not used. Therefore, it was possible to perform an analysis of the Kalman filter importance applied to an aerobraking maneuver.
AreaETES
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doc Directory Contentaccess
source Directory Contentthere are no files
agreement Directory Contentthere are no files
4. Conditions of access and use
Languageen
User Groupadministrator
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Reader Groupadministrator
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Visibilityshown
Archiving Policydenypublisher allowfinaldraft
Read Permissiondeny from all and allow from 150.163
Update Permissionnot transferred
5. Allied materials
Mirror Repositoryiconet.com.br/banon/2006/11.26.21.31
Next Higher Units8JMKD3MGPCW/3F2UALS
8JMKD3MGPCW/446AF4B
Citing Item Listsid.inpe.br/mtc-m21/2012/07.13.14.45.41 2
sid.inpe.br/mtc-m21/2012/07.13.14.49.46 2
sid.inpe.br/bibdigital/2021/02.11.18.06 2
DisseminationWEBSCI; PORTALCAPES; COMPENDEX; SCOPUS.
Host Collectionsid.inpe.br/mtc-m21b/2013/09.26.14.25.20
6. Notes
Empty Fieldsalternatejournal archivist callnumber copyholder copyright creatorhistory descriptionlevel format isbn lineage mark month nextedition notes number orcid pages parameterlist parentrepositories previousedition previouslowerunit progress project rightsholder schedulinginformation secondarydate secondarykey session shorttitle sponsor subject targetfile tertiarymark tertiarytype url
7. Description control
e-Mail (login)marcelo.pazos@inpe.br
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