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1. Identity statement
Reference TypeBook Section
Sitemtc-m21c.sid.inpe.br
Holder Codeisadg {BR SPINPE} ibi 8JMKD3MGPCW/3DT298S
Identifier8JMKD3MGP3W34R/3SMUC5H
Repositorysid.inpe.br/mtc-m21c/2019/02.08.17.13   (restricted access)
Last Update2019:02.08.17.13.10 (UTC) simone
Metadata Repositorysid.inpe.br/mtc-m21c/2019/02.08.17.13.10
Metadata Last Update2020:01.06.11.42.09 (UTC) administrator
Secondary KeyINPE--/
DOI10.1007/978-3-319-99268-6_38
Citation KeyRomeroSouz:2019:SaCoSy
TitleSatellite controller system based on reaction wheels using the State-Dependent Riccati Equation (SDRE) on Java
Year2019
Access Date2024, May 19
Secondary TypePRE LI
Number of Files1
Size1492 KiB
2. Context
Author1 Romero, Alessandro Gerlinger
2 Souza, Luiz Carlos Gadelha de
Resume Identifier1
2 8JMKD3MGP5W/3C9JHN3
Group1 CMC-ETES-SESPG-INPE-MCTIC-GOV-BR
Affiliation1 Instituto Nacional de Pesquisas Espaciais (INPE)
2 Universidade Federal do ABC (UFABC)
Author e-Mail Address1 romgerale@yahoo.com.br
2 luiz.gadelha@ufabc.edu.br
EditorCavalca, Katia Lucchesi
Weber, Hans Ingo
Book TitleProceedings of the 10th International Conference on Rotor Dynamics - IFToMM
PublisherSpringer
Pages547-561
History (UTC)2019-02-08 17:13:36 :: simone -> administrator :: 2019
2020-01-06 11:42:09 :: administrator -> simone :: 2019
3. Content and structure
Is the master or a copy?is the master
Content Stagecompleted
Transferable1
Content TypeExternal Contribution
Version Typepublisher
KeywordsNonlinear control · SDRE · Satellite · Attitude Reaction wheels
AbstractComplex space missions involving large angle maneuvers and fast attitude control require nonlinear control methods to design the Satellite Controller System (SCS) in order to satisfy robustness and performance requirements. One candidate method for a nonlinear SCS control law is the State-Dependent Riccati Equation (SDRE). SDRE provides an effective algorithm for synthesizing nonlinear feedback control by allowing nonlinearities in the system states while offering great design flexibility through state-dependent weighting matrices. In that context, analysis by simulation of nonlinear control methods can save money and time. Although, commercial 3D simulators exist that can accommodate various satellites components including the controllers, in this paper, we present a 3D simulator and the investigation of a SDRE control law performance by simulations. The simulator is implemented based on Java and related open-source software libraries (Hipparchus - linear algebra library, and Orekit - flight dynamics library), therefore, it can run in a variety of platforms and it has low cost. These open-source libraries were extended in order to solve the optimization problem that is the cornerstone of the SDRE method, a major contribution of the simulator. The simulator is evaluated taking into account a typical mission of the Brazilian National Institute for Space Research (INPE), in which the SCS must stabilize a satellite in three-axis using reaction wheels so that the optical payload can point to the desired target. Two SCS control laws (a linear and a SDRE based) were simulated for an attitude maneuver in the launch and early orbit phase (LEOP), the upside-down maneuver. The results of simulations shown that SDRE-based controller provides better performance.
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4. Conditions of access and use
Languageen
Target Fileromero_satelllite.pdf
User Groupsimone
Reader Groupadministrator
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Visibilityshown
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5. Allied materials
Next Higher Units8JMKD3MGPCW/3F2UALS
Citing Item Listsid.inpe.br/mtc-m21/2012/07.13.14.54.10 5
sid.inpe.br/bibdigital/2013/10.14.00.13 1
DisseminationBNDEPOSITOLEGAL
Host Collectionurlib.net/www/2017/11.22.19.04
6. Notes
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