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The search expression was <secondaryty pi and firstg DMC-ETE-INPE-MCTI-GOV-BR and y 2012 and dissemination websci>.
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Search local date and time: 31/01/2023 06:32.
1. Identity statement
Reference TypeJournal Article
Siteplutao.sid.inpe.br
Holder Codeisadg {BR SPINPE} ibi 8JMKD3MGPCW/3DT298S
IdentifierJ8LNKAN8RW/3D537A2
Repositorydpi.inpe.br/plutao/2012/11.28.14.05.33
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Secondary KeyINPE--PRE/
DOI10.1111/j.1365-2966.2012.21101.x
ISSN1365-2966
Labellattes: 7340081273816424 3 AraujoWintPradSukh:2012:StReAr
Citation KeyAraujoWintPradSukh:2012:StReAr
TitleStability regions around the components of the triple system 2001 SN263
Year2012
MonthJuly
Access Date2023, Jan. 31
Secondary TypePRE PI
Number of Files1
Size4455 KiB
2. Context
Author1 Araujo, R. A. N.
2 Winter, Othon Cabo
3 Prado, Antonio Fernando Bertachini de Almeida
4 Sukhanov, A.
Resume Identifier1
2
3 8JMKD3MGP5W/3C9JGJA
Group1
2
3 DMC-ETE-INPE-MCTI-GOV-BR
Affiliation1 UNESP - São Paulo State University, CEP 12516-410 Guaratinguetá, SP, Brazil
2 UNESP - São Paulo State University, CEP 12516-410 Guaratinguetá, SP, Brazil
3 Instituto Nacional de Pesquisas Espaciais (INPE)
Author e-Mail Address1
2
3 prado@dem.inpe.br
e-Mail Addressprado@dem.inpe.br
JournalMonthly Notices of the Royal Astronomical Society
Volume423
Number4
Pages3058-3073
Secondary MarkA2_ASTRONOMIA_/_FÍSICA A1_ENGENHARIAS_III C_ENSINO_DE_CIÊNCIAS_E_MATEMATICA A1_INTERDISCIPLINAR A2_MATEMÁTICA_/_PROBABILIDADE_E_ESTATÍSTICA A1_QUÍMICA
History (UTC)2012-11-28 23:06:21 :: lattes -> administrator :: 2012
2012-11-30 13:52:23 :: administrator -> marciana :: 2012
2012-12-13 18:30:13 :: marciana -> administrator :: 2012
2013-01-20 15:54:19 :: administrator -> marciana :: 2012
2013-01-28 13:09:35 :: marciana -> administrator :: 2012
2021-02-11 18:11:14 :: administrator -> marciana :: 2012
3. Content and structure
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Content TypeExternal Contribution
Version Typepublisher
Keywordscelestial mechanics
N-body simulations
minor planets
asteroids
astrodinâmica
manobras orbitais
trajetórias espaciais
AbstractSpace missions are an excellent way to increase our knowledge of asteroids. Near-Earth asteroids (NEAs) are good targets for such missions, as they periodically approach the orbit of the Earth. Thus, an increasing number of missions to NEAs are being planned worldwide. Recently, NEA (153591) 2001 SN263 was chosen as the target of the ASTER MISSION - the First Brazilian Deep Space Mission, with launch planned for 2015. NEA (153591) 2001 SN263 was discovered in 2001. In 2008 February, radio astronomers from Arecibo-Puerto Rico concluded that (153591) 2001 SN263 is actually a triple system. The announcement of ASTER MISSION has motivated the development of the present work, whose goal is to characterize regions of stability and instability of the triple system (153591) 2001 SN263. Understanding and characterizing the stability of such a system is an important component in the design of the mission aiming to explore it. The method adopted consisted of dividing the region around the system into four distinct regions (three of them internal to the system and one external). We performed numerical integrations of systems composed of seven bodies, namely the Sun, Earth, Mars, Jupiter and the three components of the asteroid system (Alpha, the most massive body; Beta the second most massive body; and Gamma, the least massive body), and of thousands of particles randomly distributed within the demarcated regions, for the planar and inclined prograde cases. The results are displayed as diagrams of semi-major axis versus eccentricity that show the percentage of particles that survive for each set of initial conditions. The regions where 100per cent of the particles survive are defined as stable regions. We found that the stable regions are in the neighbourhood of Alpha and Beta, and in the external region. Resonant motion of the particles with Beta and Gamma was identified in the internal regions, leading to instability. For particles with I > 45° in the internal region, where I is the inclination with respect to Alpha's equator, there is no stable region, except for particles placed very close to Alpha. The stability in the external region is not affected by the variation of inclination. We also present a discussion of the long-term stability in the internal region, for the planar and circular case, with comparisons with the short-term stability.
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1. Identity statement
Reference TypeJournal Article
Siteplutao.sid.inpe.br
Holder Codeisadg {BR SPINPE} ibi 8JMKD3MGPCW/3DT298S
IdentifierJ8LNKAN8RW/3C63KPK
Repositorydpi.inpe.br/plutao/2012/06.21.18.26.23   (restricted access)
Last Update2012:08.24.12.32.38 (UTC) administrator
Metadata Repositorydpi.inpe.br/plutao/2012/06.21.18.26.24
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Secondary KeyINPE--PRE/
DOI10.1016/j.asr.2011.11.036
ISSN0273-1177
Labellattes: 7340081273816424 4 CarvalhoElipVilhPrad:2012:LoNeNe
Citation KeyCarvalhoElipVilhPrad:2012:LoNeNe
TitleLow-altitude, near-polar and near-circular orbits around Europa
Year2012
MonthMar.
Access Date2023, Jan. 31
Secondary TypePRE PI
Number of Files1
Size2347 KiB
2. Context
Author1 Carvalho, J. P. S.
2 Elipe, A
3 Vilhena de Moraes, R.
4 Prado, Antonio Fernando Bertachini de Almeida
Resume Identifier1
2
3
4 8JMKD3MGP5W/3C9JGJA
Group1
2
3
4 DMC-ETE-INPE-MCTI-GOV-BR
Affiliation1 UNESP – Univ Estadual Paulista / UNIFESP – Instituto de Ciencia e Tecnologia, Universidade Federal de Sao Paulo
2 Centro Universitario de la Defensa de Zaragoza, and Grupo de Meca´ nica Espacial-IUMA, Universidad de Zaragoza, Spain
3 UNESP – Univ Estadual Paulista / UNIFESP – Instituto de Ciencia e Tecnologia, Universidade Federal de Sao Paulo
4 Instituto Nacional de Pesquisas Espaciais (INPE)
Author e-Mail Address1 jeanfeg@gmail.com
2
3 rodolpho.vilhena@gmail.com
4 abertachini@terra.com.br
e-Mail Addressabertachini@terra.com.br
JournalAdvances in Space Research
Volume49
Number5
Pages994-1006
Secondary MarkB4_ASTRONOMIA_/_FÍSICA B3_CIÊNCIAS_BIOLÓGICAS_I B1_ENGENHARIAS_III B1_ENGENHARIAS_IV B1_GEOCIÊNCIAS B1_INTERDISCIPLINAR
History (UTC)2012-06-22 00:10:59 :: lattes -> administrator :: 2012
2012-07-26 23:30:14 :: administrator -> secretaria.cpa@dir.inpe.br :: 2012
2012-08-24 12:32:38 :: secretaria.cpa@dir.inpe.br -> administrator :: 2012
2012-08-30 08:06:48 :: administrator -> secretaria.cpa@dir.inpe.br :: 2012
2012-08-30 16:01:40 :: secretaria.cpa@dir.inpe.br -> administrator :: 2012
2012-09-28 21:26:36 :: administrator -> secretaria.cpa@dir.inpe.br :: 2012
2013-01-20 15:33:25 :: secretaria.cpa@dir.inpe.br -> banon :: 2012
2013-01-20 15:34:52 :: banon -> administrator :: 2012
2013-01-20 15:53:03 :: administrator -> banon :: 2012
2013-02-18 14:23:46 :: banon -> administrator :: 2012
2021-02-11 18:11:12 :: administrator -> marciana :: 2012
3. Content and structure
Is the master or a copy?is the master
Content Stagecompleted
Transferable1
Content TypeExternal Contribution
Version Typepublisher
KeywordsAstrodinâmica
Manobras Orbitais
Trajetórias Espaciais
AbstractThe dynamics of orbits around planetary satellites, taking into account the gravitational attraction of a third-body and the non -uniform distribution of mass of the planetary satellite, is studied. The Hamiltonian considered is explicitly time-dependent. Conditions for frozen orbits are presented. Low-altitude, near-polar orbits, very desirable for scientific missions to study planetary satellites such as the Jupiters moon Europa, are analyzed. Lifetimes for these orbits are computed through the single and double averaged method. Comparison between the results obtained by the single and double averaged method is presented. The single-averaged model is more realistic, since it does not eliminate the term due to the equatorial ellipticity of the planetary satellite as done by the double-averaged problem. Considering the single-averaged method, we found unstable frozen orbits where the satellite does not impact with the surface of Europa for at least 200 days. We present an approach using the unaveraged disturbing potential to analyze the effects of these terms in the amplitude of the eccentricity.
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Target FileCarvalho_et_al_2012.pdf
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6. Notes
Empty Fieldsalternatejournal archivist callnumber copyholder copyright creatorhistory descriptionlevel format isbn lineage mark mirrorrepository nextedition notes orcid parameterlist parentrepositories previousedition previouslowerunit progress project rightsholder secondarydate session shorttitle sponsor subject tertiarymark tertiarytype typeofwork url
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1. Identity statement
Reference TypeJournal Article
Siteplutao.sid.inpe.br
Holder Codeisadg {BR SPINPE} ibi 8JMKD3MGPCW/3DT298S
IdentifierJ8LNKAN8RW/3D537AE
Repositorydpi.inpe.br/plutao/2012/11.28.14.05.45   (restricted access)
Last Update2013:03.01.19.18.21 (UTC) administrator
Metadata Repositorydpi.inpe.br/plutao/2012/11.28.14.05.46
Metadata Last Update2021:02.11.18.11.15 (UTC) administrator
Secondary KeyINPE--PRE/
DOI10.1142/S0218127412502409
ISSN0218-1274
1793-6551
Labellattes: 7340081273816424 5 CarvalhoMouEliMorPra:2012:FRORAR
Citation KeyCarvalhoMouEliMorPra:2012:FrOrAr
TitleFrozen orbits around Europa
ProjectFAPESP (2007/04413-7), (2011/05671-5), (2011/09310-7); Edital 14/2011-PROPe, CNPQ (303070/2011-0); Spanish Government (Project # AYA2008-05572)
Year2012
MonthOct.
Access Date2023, Jan. 31
Secondary TypePRE PI
Number of Files1
Size2533 KiB
2. Context
Author1 Carvalho, Jean P S
2 Mourão, D. C.
3 Elipe, A
4 Moraes, R. Vilhena
5 Prado, Antonio Fernando Bertachini de Almeida
Resume Identifier1
2
3
4
5 8JMKD3MGP5W/3C9JGJA
Group1
2
3
4
5 DMC-ETE-INPE-MCTI-GOV-BR
Affiliation1 UNESP Univ Estadual Paulista, CEP. 12.516-410 Guaratinguetá SP, Brazil
2 UNESP, Univ Estadual Paulista, CEP. 12.516-410 Guaratinguetá SP, Brazil
3 Centro Universitario de la Defensa and GME-IUMA, Universidad de Zaragoza, Spain
4 UNESP Univ Estadual Paulista, CEP. 12.516-410 Guaratinguetá SP, Brazil
5 Instituto Nacional de Pesquisas Espaciais (INPE)
Author e-Mail Address1 jeanfeg@gmail.com
2 decmou@yahoo.com.br
3 elipe@unizar.es
4 rodolpho.vilhena@gmail.com
5 prado@dem.inpe.br
e-Mail Addressprado@dem.inpe.br
JournalInternational Journal of Bifurcation and Chaos
Volume22
Number10
Pages1250240
History (UTC)2012-11-28 23:06:21 :: lattes -> marciana :: 2012
2012-12-03 12:41:29 :: marciana -> administrator :: 2012
2013-01-30 13:11:36 :: administrator -> marciana :: 2012
2013-01-30 13:13:01 :: marciana -> administrator :: 2012
2013-01-30 14:36:59 :: administrator -> marciana :: 2012
2013-03-01 19:18:21 :: marciana -> administrator :: 2012
2021-02-11 18:11:15 :: administrator -> marciana :: 2012
3. Content and structure
Is the master or a copy?is the master
Content Stagecompleted
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Content TypeExternal Contribution
Version Typepublisher
Keywordsartificial satellite
frozen orbits
orbital perturbations
planetary satellites
AbstractLow-altitude, near-polar orbits are very desirable for scientific missions to study the natural satellites of the planets of the Solar System, such as Europa, that is one of the natural satellites of Jupiter. The problem is analyzed considering that an artificial satellite is orbiting Europa and that this spacecraft is perturbed by the nonuniform distribution of mass of the planetary satellite (J 2, J 3, C 22) and by the gravitational attraction of the third-body. We present an analytical theory using the averaged model and applications were done by performing numerical integrations of the analytical equations developed. Using the averaged method, several frozen orbits were obtained. Some of them has low inclination, low altitude and long lifetime. Numerical simulations are performed using the software Mercury, to compare the results obtained using the analytical theory.
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ArrangementFrozen orbits around...
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DisseminationWEBSCI; PORTALCAPES.
Host Collectiondpi.inpe.br/plutao@80/2008/08.19.15.01
6. Notes
Empty Fieldsalternatejournal archivist callnumber copyholder copyright creatorhistory descriptionlevel format isbn lineage mark mirrorrepository nextedition notes orcid parameterlist parentrepositories previousedition previouslowerunit progress rightsholder secondarydate secondarymark session shorttitle sponsor subject tertiarymark tertiarytype typeofwork url
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1. Identity statement
Reference TypeJournal Article
Sitemtc-m16d.sid.inpe.br
Holder Codeisadg {BR SPINPE} ibi 8JMKD3MGPCW/3DT298S
Identifier8JMKD3MGP7W/3CEUL6P
Repositorysid.inpe.br/mtc-m19/2012/08.15.16.11   (restricted access)
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Metadata Repositorysid.inpe.br/mtc-m19/2012/08.15.16.11.48
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Secondary KeyINPE--PRE/
DOI10.1155/2012/768973
ISSN1024-123X
1563-5147
Citation KeyChiaradiaKugaPrad:2012:CoTwMe
TitleComparison between Two Methods to Calculate the Transition Matrix of Orbit Motion
Year2012
Access Date2023, Jan. 31
Secondary TypePRE PI
Number of Files1
Size511 KiB
2. Context
Author1 Chiaradia, Ana Paula Marins
2 Kuga, Hélio Koiti
3 Prado, Antonio Fernando Bertachini de Almeida
Resume Identifier1
2 8JMKD3MGP5W/3C9JHC9
3 8JMKD3MGP5W/3C9JGJA
Group1
2 DMC-ETE-INPE-MCTI-GOV-BR
3 DMC-ETE-INPE-MCTI-GOV-BR
Affiliation1 Grupo de Dinâmica Orbital e Planetologia, Departament of Mathematics, FEG/UNESP, CEP 12516-410, Guaratinguetá, SP, Brazil
2 Instituto Nacional de Pesquisas Espaciais (INPE)
3 Instituto Nacional de Pesquisas Espaciais (INPE)
JournalMathematical Problems in Engineering
Volume2012
NumberArticle ID 768973
Secondary MarkB5_ASTRONOMIA_/_FÍSICA B4_CIÊNCIA_DA_COMPUTAÇÃO B3_CIÊNCIAS_AGRÁRIAS_I B1_ENGENHARIAS_I B2_ENGENHARIAS_II B1_ENGENHARIAS_III A2_ENGENHARIAS_IV A2_INTERDISCIPLINAR B3_MATEMÁTICA_/_PROBABILIDADE_E_ESTATÍSTICA
History (UTC)2012-08-15 16:11:48 :: marciana -> administrator ::
2012-08-15 16:11:49 :: administrator -> marciana :: 2012
2012-08-15 16:14:38 :: marciana -> administrator :: 2012
2012-08-24 12:43:49 :: administrator -> marciana :: 2012
2012-12-14 10:54:56 :: marciana -> administrator :: 2012
2021-02-11 18:10:30 :: administrator -> marciana :: 2012
3. Content and structure
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AbstractTwo methods to evaluate the state transition matrix are implemented and analyzed to verify the computational cost and the accuracy of both methods. This evaluation represents one of the highest computational costs on the artificial satellite orbit determination task. The first method is an approximation of the Keplerian motion, providing an analytical solution which is then calculated numerically by solving Kepler's equation. The second one is a local numerical approximation that includes the effect of 𝐽 2 . The analysis is performed comparing these two methods with a reference generated by a numerical integrator. For small intervals of time (1 to 10 s) and when one needs more accuracy, it is recommended to use the second method, since the CPU time does not excessively overload the computer during the orbit determination procedure. For larger intervals of time and when one expects more stability on the calculation, it is recommended to use the first method.
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Arrangementurlib.net > BDMCI > Fonds > Produção > DIDMC > Comparison between Two...
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LinkingTrabalho Vinculado à Tese/Dissertação
Mirror Repositorysid.inpe.br/mtc-m19@80/2009/08.21.17.02.53
Next Higher Units8JMKD3MGPCW/446AF4B
DisseminationWEBSCI; PORTALCAPES; COMPENDEX.
Host Collectionsid.inpe.br/mtc-m19@80/2009/08.21.17.02
6. Notes
Empty Fieldsalternatejournal archivist callnumber copyholder copyright creatorhistory descriptionlevel e-mailaddress electronicmailaddress format isbn keywords label lineage mark month nextedition notes orcid pages parameterlist parentrepositories previousedition previouslowerunit progress project rightsholder secondarydate session shorttitle sponsor subject tertiarytype typeofwork url
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1. Identity statement
Reference TypeJournal Article
Siteplutao.sid.inpe.br
Holder Codeisadg {BR SPINPE} ibi 8JMKD3MGPCW/3DT298S
IdentifierJ8LNKAN8RW/3C63NL3
Repositorydpi.inpe.br/plutao/2012/06.21.19.01.13
Last Update2012:08.24.16.24.24 (UTC) administrator
Metadata Repositorydpi.inpe.br/plutao/2012/06.21.19.01.14
Metadata Last Update2021:02.11.18.11.13 (UTC) administrator
DOI10.3233/SAV-2012-0702
ISSN1070-9622
Labellattes: 5801699053436537 2 Mainenti-LopesSouzSous:2012:DeNoCo
Citation KeyMainenti-LopesSouzSous:2012:DeNoCo
TitleDesign of a nonlinear controller for a rigid-flexible satellite using multi-objective Generalized Extremal Optimization with real codification
Year2012
Access Date2023, Jan. 31
Secondary TypePRE PI
Number of Files1
Size494 KiB
2. Context
Author1 Mainenti-Lopes, Igor
2 Souza, Luiz Carlos Gadelha de
3 Sousa, Fabiano Luis de
Resume Identifier1
2 8JMKD3MGP5W/3C9JHN3
3 8JMKD3MGP5W/3C9JH3H
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)
Author e-Mail Address1
2 gadelha@dem.inpe.br
e-Mail Addressgadelha@dem.inpe.br
JournalShock and Vibration
Volume19
Number5
Pages1-10
Secondary MarkB1_ENGENHARIAS_I B1_ENGENHARIAS_III B2_ENGENHARIAS_IV B1_INTERDISCIPLINAR
History (UTC)2012-06-22 00:10:59 :: lattes -> secretaria.cpa@dir.inpe.br :: 2012
2012-08-24 16:24:24 :: secretaria.cpa@dir.inpe.br -> administrator :: 2012
2012-10-19 20:26:57 :: administrator -> secretaria.cpa@dir.inpe.br :: 2012
2012-12-14 11:59:05 :: secretaria.cpa@dir.inpe.br -> administrator :: 2012
2021-02-11 18:11:13 :: administrator -> marciana :: 2012
3. Content and structure
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Content Stagecompleted
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Content TypeExternal Contribution
Version Typefinaldraft
KeywordsDynamic and control of flexible system
optimization algorithm
AbstractThe Attitude Control System (ACS) for Flexible Space Structures (FSS) like rigid-flexible satellite and solar sails demands great reliability, autonomy and robustness. The association of flexible motion and large angle maneuver imply that the FSS dynamics is only captured by complex non-linear mathematical model. As a result, FSS controller performance designed by linear control technique under the hypothesis of rigid dynamic can be degraded. Although vibrations can be suppressed rapidly, the flexibility effect can introduce a tracking error resulting in a minimum attitude acquisition time. On the other hand, faster manoeuvres can excite flexible modes in such a way to make the FSS lose the required pointing accuracy. In the present work, it is shown that a new multi-objective optimization algorithm, called M-GEOreal (Multi-objective Generalized Extremal Optimization with real codification), is a good tool to be used in such kind of problems. The M-GEOreal is a real coded version of the M-GEO evolutionary algorithm. Its performance on finding the gains of a non linear control law is evaluated through its application to the problem of controlling a large angle attitude manoeuvre of a rigid-flexible satellite. The satellite non-linear model consists of a rigid central hub with a clamped free flexible beam. The multi-objective approach allows optimizing conflicting objective functions like time and energy. As a result, one can find a trade-off solution (non-dominated solutions). These solutions become available to the designer for posterior choice of an individual solution to be implemented. The non-dominated solutions are represented in the design space (Pareto set) and in the objective functions space (Pareto front). Having in mind the complexity of implementing a control algorithm in onboard satellite computer, this preliminary investigation has shown that the non-linear controller based on the M-GEOreal algorithm is a promising technique, since it has satisfied all the ACS requirements. A great advantage of the M-GEOreal procedure is its capacity to deal with non-linear system and designing non-linear controller with constant gains facilitating the on board computer implementation.
AreaETES
Arrangementurlib.net > BDMCI > Fonds > Produção anterior à 2021 > DIDMC > Design of a...
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data URLhttp://urlib.net/ibi/J8LNKAN8RW/3C63NL3
zipped data URLhttp://urlib.net/zip/J8LNKAN8RW/3C63NL3
Languageen
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LinkingTrabalho Vinculado à Tese/Dissertação
Next Higher Units8JMKD3MGPCW/446AF4B
DisseminationWEBSCI; PORTALCAPES.
Host Collectiondpi.inpe.br/plutao@80/2008/08.19.15.01
6. Notes
NotesSetores de Atividade: Atividades profissionais, científicas e técnicas.
Empty Fieldsalternatejournal archivist callnumber copyholder copyright creatorhistory descriptionlevel format isbn lineage mark mirrorrepository month nextedition orcid parameterlist parentrepositories previousedition previouslowerunit progress project rightsholder secondarydate secondarykey session shorttitle sponsor subject tertiarytype typeofwork url
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1. Identity statement
Reference TypeJournal Article
Siteplutao.sid.inpe.br
Holder Codeisadg {BR SPINPE} ibi 8JMKD3MGPCW/3DT298S
IdentifierJ8LNKAN8RW/3C63NKH
Repositorydpi.inpe.br/plutao/2012/06.21.19.01   (restricted access)
Last Update2012:08.28.11.34.45 (UTC) administrator
Metadata Repositorydpi.inpe.br/plutao/2012/06.21.19.01.12
Metadata Last Update2021:02.11.18.11.13 (UTC) administrator
ISSN0065-3438
Labellattes: 5801699053436537 1 SouzaAren:2012:DeSaCo
Citation KeySouzaAren:2012:DeSaCo
TitleDesign of Satellite Control Algorihtm Using the State Dependent Ricatti Equation and Kalman Filter
Year2012
Access Date2023, Jan. 31
Secondary TypePRE PI
Number of Files1
Size129 KiB
2. Context
Author1 Souza, Luiz Carlos Gadelha de
2 Arena, Victor M. R.
Resume Identifier1 8JMKD3MGP5W/3C9JHN3
Group1 DMC-ETE-INPE-MCTI-GOV-BR
Affiliation1 Instituto Nacional de Pesquisas Espaciais (INPE)
2 Federal University of ABC, Santo André, São Paulo, Brazil
Author e-Mail Address1 gadelha@dem.inpe.br
2 varena@aluno.ufabc.edu.br
e-Mail Addressgadelha@dem.inpe.br
JournalAdvances in the Astronautical Sciences
VolumeI
Number2
Pages235-243
Secondary MarkB3_ENGENHARIAS_III
History (UTC)2012-06-22 00:10:59 :: lattes -> secretaria.cpa@dir.inpe.br :: 2012
2012-08-28 11:34:46 :: secretaria.cpa@dir.inpe.br -> administrator :: 2012
2013-01-20 15:53:18 :: administrator -> banon :: 2012
2013-02-18 14:44:55 :: banon -> administrator :: 2012
2021-02-11 18:11:13 :: administrator -> marciana :: 2012
3. Content and structure
Is the master or a copy?is the master
Content Stagecompleted
Transferable1
Content TypeExternal Contribution
KeywordsRobust Control System
State Dependent Ricatti Equation
AbstractA properly attitude control algorithm design and test procedure can dramatically minimize space mission costs by reducing the number of errors that can be transmitted to the next phase of the project. Besides, when attitude control algorithm problems are discovered on-orbit the mission or at least part of it can be lost. One way to increase confidence in the control algorithm is its experimental validation through prototypes. The Space Mechanics and Control Division (DMC) of INPE is constructing a 3D simulator to supply the conditions for implementing and testing satellite hardware and software. The 3D simulator can accommodate various satellites components; like sensors, actuators, computers and its respective interface and electronic. Depending on the manoeuvre the 3D simulator plant can be highly non-linear and if its inertia parameters are not well determined the plant can also present some kind of uncertainty. As a result, controller designed by linear control technique can have its performance and robustness degraded. This paper presents the application of the State-Dependent Riccati Equation (SDRE) method in conjunction with Kalman filter to design and test a attitude control algorithm for a 3D satellite simulator. The control strategy is based on gas jets and reaction wheel torques to perform large angle manoeuvre in three axes. The simulator model allows investigating the dynamics and the control system taking into account effects of the plant non-linearities and system noise. Initially, a simple comparison between the LQR and SDRE controller is performed. Practical applications are presented to address problems like presence of noise in process and measurements and incomplete state information using Kalman filter technique. Simulation has shown the performance and robustness of the SDRE controller applied for angular velocity reduction associated with stringent pointing requirement.
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6. Notes
NotesSetores de Atividade: Atividades profissionais, científicas e técnicas.
Empty Fieldsalternatejournal archivist callnumber copyholder copyright creatorhistory descriptionlevel doi format isbn lineage mark mirrorrepository month nextedition orcid parameterlist parentrepositories previousedition previouslowerunit progress project rightsholder secondarydate secondarykey session shorttitle sponsor subject targetfile tertiarymark tertiarytype typeofwork versiontype
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1. Identity statement
Reference TypeJournal Article
Siteplutao.sid.inpe.br
Holder Codeisadg {BR SPINPE} ibi 8JMKD3MGPCW/3DT298S
IdentifierJ8LNKAN8RW/3C63NL5
Repositorydpi.inpe.br/plutao/2012/06.21.19.01.15
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DOI10.3233/SAV-2012-0701
ISSN1070-9622
Labellattes: 5801699053436537 1 SouzaGonz:2012:ApStRi
Citation KeySouzaGonz:2012:ApStRi
TitleApplication of the state-dependent riccati equation and kalman filter techniques to the design of a satellite control system
Year2012
Access Date2023, Jan. 31
Secondary TypePRE PI
Number of Files1
Size563 KiB
2. Context
Author1 Souza, Luiz Carlos Gadelha de
2 Gonzales, R G
Resume Identifier1 8JMKD3MGP5W/3C9JHN3
Group1 DMC-ETE-INPE-MCTI-GOV-BR
Affiliation1 Instituto Nacional de Pesquisas Espaciais (INPE)
Author e-Mail Address1 gadelha@dem.inpe.br
e-Mail Addressgadelha@dem.inpe.br
JournalShock and Vibration
Volume19
Number5
Pages22-28
Secondary MarkB1_ENGENHARIAS_I B1_ENGENHARIAS_III B2_ENGENHARIAS_IV B1_INTERDISCIPLINAR
History (UTC)2012-06-22 00:11:00 :: lattes -> secretaria.cpa@dir.inpe.br :: 2012
2012-08-27 17:18:31 :: secretaria.cpa@dir.inpe.br -> administrator :: 2012
2012-10-19 20:26:57 :: administrator -> secretaria.cpa@dir.inpe.br :: 2012
2013-01-18 11:03:57 :: secretaria.cpa@dir.inpe.br -> administrator :: 2012
2021-02-11 18:11:13 :: administrator -> marciana :: 2012
3. Content and structure
Is the master or a copy?is the master
Content Stagecompleted
Transferable1
Content TypeExternal Contribution
Version Typefinaldraft
KeywordsSatellite simulator
SDRE methodology
robust control
AbstractDesign of Satellite Attitude Control System (ACS) that involves plant uncertainties and large angle manoeuvres following a stringent pointing control, may require new non-linear control techniques in order to have adequate stability, good performance and robustness. In that context, experimental validation of new non-linear control techniques through prototypes is the way to increase confidence in the controller designed. The Space Mechanics and Control Division (DMC) of INPE is constructing a 3-D simulator to supply the conditions for implementing and testing satellite ACS hardware and software. The 3-D simulator can accommodate various satellites components; like sensors, actuators, computers and its respective interface and electronic. Depending on the manoeuvre the 3-D simulator plant can be highly non-linear and if the simulator inertia parameters are not well determined the plant also can present some kind of uncertainty. As a result, controller designed by linear control technique can have its performance and robustness degraded, therefore controllers designed by new non-linear approach must be considered. This paper presents the application of the State-Dependent Riccati Equation (SDRE) method in conjunction with Kalman filter technique to design a controller for the DMC 3-D satellite simulator. The SDRE can be considered as the non-linear counterpart of Linear Quadratic Regulator (LQR) control technique. Initially, a simple comparison between the LQR and SDRE controller is performed. After that, practical applications are presented to address problems like presence of noise in process and measurements and incomplete state information. Kalman filter is considered as state observer to address these issues. The effects of the plant non-linearities and noises (uncertainties) are considered in the performance and robustness of the controller designed by the SDRE and Kalman filter. The 3-D simulator simulink-based model has been developed to perform the simulations examples to investigate the SDRE controller performance using the states estimated by the Kalman filter. Simulations have demonstrated the validity of the proposed approach, once the SDRE controller has presented good stability margin, great performance and robustness.
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data URLhttp://urlib.net/ibi/J8LNKAN8RW/3C63NL5
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Next Higher Units8JMKD3MGPCW/446AF4B
DisseminationWEBSCI; PORTALCAPES.
Host Collectiondpi.inpe.br/plutao@80/2008/08.19.15.01
6. Notes
NotesSetores de Atividade: Atividades profissionais, científicas e técnicas.
Empty Fieldsalternatejournal archivist callnumber copyholder copyright creatorhistory descriptionlevel format isbn lineage mark mirrorrepository month nextedition orcid parameterlist parentrepositories previousedition previouslowerunit progress project rightsholder secondarydate secondarykey session shorttitle sponsor subject tertiarytype typeofwork url
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1. Identity statement
Reference TypeJournal Article
Siteplutao.sid.inpe.br
Holder Codeisadg {BR SPINPE} ibi 8JMKD3MGPCW/3DT298S
IdentifierJ8LNKAN8RW/3D537AA
Repositorydpi.inpe.br/plutao/2012/11.28.14.05.41   (restricted access)
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Secondary KeyINPE--PRE/
DOI10.1016/j.asr.2012.07.028
ISSN0273-1177
Labellattes: 7340081273816424 2 SukhanovPrad:2012:OnApOp
Citation KeySukhanovPrad:2012:OnApOp
TitleOn one approach to the optimization of low-thrust station keeping manoeuvres
Year2012
MonthDec.
Access Date2023, Jan. 31
Secondary TypePRE PI
Number of Files1
Size707 KiB
2. Context
Author1 Sukhanov, A. A.
2 Prado, Antonio Fernando Bertachini de Almeida
Resume Identifier1
2 8JMKD3MGP5W/3C9JGJA
Group1
2 DMC-ETE-INPE-MCTI-GOV-BR
Affiliation1 Space Research Institute (IKI) of the Russian Academy of Sciences, 117997, 84/32 Profsoyuznaya Str, Moscow, Russia
2 Instituto Nacional de Pesquisas Espaciais (INPE)
Author e-Mail Address1
2 prado@dem.inpe.br
e-Mail Addressprado@dem.inpe.br
JournalAdvances in Space Research
Volume50
Number11
Pages1478-1488
Secondary MarkB4_ASTRONOMIA_/_FÍSICA B3_CIÊNCIAS_BIOLÓGICAS_I B1_ENGENHARIAS_III B1_ENGENHARIAS_IV B1_GEOCIÊNCIAS B1_INTERDISCIPLINAR
History (UTC)2012-11-28 23:06:21 :: lattes -> administrator :: 2012
2012-11-29 12:50:33 :: administrator -> marciana :: 2012
2012-11-29 13:02:23 :: marciana -> administrator :: 2012
2013-02-05 21:02:32 :: administrator -> banon :: 2012
2013-02-18 14:43:25 :: banon -> administrator :: 2012
2021-02-11 18:11:15 :: administrator -> marciana :: 2012
3. Content and structure
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Content TypeExternal Contribution
Version Typepublisher
KeywordsAstrodinâmica
Manobras Orbitais
Manobras Espaciais
AbstractA simple and effective mathematical method to calculate optimal station-keeping manoeuvres by means of electric propulsion is suggested. The method is based on a linearization of the satellite motion near a reference orbit. Two versions of the method allow station keeping both in an assigned position and in any position of the orbit. The method is fully analytical for the two-body problem and takes a simpler form for the circular assigned orbit. The suggested method may also be used in the case when constraints are imposed on the thrust direction due to specific features of the satellite stabilization mode. An application of the method to any force field is shown. Illustrative examples of satellite station keeping in a circular orbit are given. Both cases of the station keeping, i.e., in an assigned position and in an assigned orbit, are considered without and with a constraint on the thrust direction.
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Arrangementurlib.net > BDMCI > Fonds > Produção anterior à 2021 > DIDMC > On one approach...
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5. Allied materials
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DisseminationWEBSCI; PORTALCAPES; MGA; COMPENDEX.
Host Collectiondpi.inpe.br/plutao@80/2008/08.19.15.01
6. Notes
Empty Fieldsalternatejournal archivist callnumber copyholder copyright creatorhistory descriptionlevel format isbn lineage mark mirrorrepository nextedition notes orcid parameterlist parentrepositories previousedition previouslowerunit progress project readergroup rightsholder secondarydate session shorttitle sponsor subject tertiarymark tertiarytype typeofwork url
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