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Search local date and time: 31/01/2023 06:22.

1. Identity statement
Reference TypeJournal Article
Siteplutao.sid.inpe.br
Holder Codeisadg {BR SPINPE} ibi 8JMKD3MGPCW/3DT298S
IdentifierJ8LNKAN8RW/3D537A6
Repositorydpi.inpe.br/plutao/2012/11.28.14.05.37   (restricted access)
Last Update2012:11.29.15.23.29 (UTC) administrator
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Secondary KeyINPE--PRE/
DOI10.1155/2012/979752
ISSN1024-123X
1563-5147
Labellattes: 7340081273816424 1 PradoZanYokWinMas:2012:MaMeAp
Citation KeyPradoZanYokWinMas:2012:MaMeAp
TitleMathematical Methods Applied to the Celestial Mechanics of Artificial Satellites
Year2012
Access Date2023, Jan. 31
Secondary TypePRE PI
Number of Files1
Size455 KiB
2. Context
Author1 Prado, Antonio Fernando Bertachini de Almeida
2 Zanardi, Maria Cecilia
3 Yokoyama, Tadashi
4 Winter, Silvia Maria Giuliatti
5 Masdemont, Josep J.
Resume Identifier1 8JMKD3MGP5W/3C9JGJA
Group1 DMC-ETE-INPE-MCTI-GOV-BR
Affiliation1 Instituto Nacional de Pesquisas Espaciais (INPE)
2 Universidade Estadual Paulista (UNESP), Campus de Guaratinguetá, CEP 12516-410 Guaratinguetá, SP, Brazil
3 Universidade Estadual Paulista, Campus de Guaratinguetá, Caixa Postal 178, 13500-970 Rio Claro, SP, Brazil
4
5 IEEC and Departament de Matemàtica Aplicada I, Universitat Politècnica de Catalunya, Diagonal 647, 08028 Barcelona, Spain
Author e-Mail Address1 prado@dem.inpe.br
e-Mail Addressprado@dem.inpe.br
JournalMathematical Problems in Engineering
Volume2012
NumberArticle ID 979752
Pages1-7
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)2012-11-28 23:06:21 :: lattes -> administrator :: 2012
2012-11-29 12:53:59 :: administrator -> marciana :: 2012
2012-12-03 12:44:54 :: 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
KeywordsAstrodinâmica
Manobras Orbitais
Engenharia Aeroespacial
AreaETES
Arrangementurlib.net > BDMCI > Fonds > Produção anterior à 2021 > DIDMC > Mathematical Methods Applied...
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6. Notes
Empty Fieldsabstract alternatejournal archivist callnumber copyholder copyright creatorhistory descriptionlevel format isbn lineage mark mirrorrepository month nextedition notes orcid parameterlist parentrepositories previousedition previouslowerunit progress project readergroup 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/3D5379Q
Repositorydpi.inpe.br/plutao/2012/11.28.14.05.28
Last Update2013:01.29.13.05.16 (UTC) administrator
Metadata Repositorydpi.inpe.br/plutao/2012/11.28.14.05.29
Metadata Last Update2021:02.11.18.11.14 (UTC) administrator
Secondary KeyINPE--PRE/
ISSN1991-8747
Labellattes: 5351862393409206 1 SantosPrad:2012:OpLoTr
Citation KeySantosPrad:2012:OpLoTr
TitleOptimal Low-Thrust Trajectories to Reach the Asteroid Apophis
Year2012
Access Date2023, Jan. 31
Secondary TypePRE PI
Number of Files1
Size890 KiB
2. Context
Author1 Santos, Denilson Paulo Souza dos
2 Prado, Antonio Fernando Bertachini de Almeida
Resume Identifier1
2 8JMKD3MGP5W/3C9JGJA
Group1
2 DMC-ETE-INPE-MCTI-GOV-BR
Affiliation1
2 Instituto Nacional de Pesquisas Espaciais (INPE)
Author e-Mail Address1 denilson@dem.inpe.br
2 prado@dem.inpe.br
e-Mail Addressdenilson@dem.inpe.br
JournalWSEAS Transactions on Applied and Theoretical Mechanics
Volume7
Number3
Pages241-251
Secondary MarkC_INTERDISCIPLINAR
History (UTC)2012-11-28 23:06:21 :: lattes -> marciana :: 2012
2012-12-14 12:37:19 :: marciana -> administrator :: 2012
2013-01-20 15:54:18 :: administrator -> marciana :: 2012
2013-01-29 13:05:16 :: marciana -> administrator :: 2012
2021-02-11 18:11:14 :: administrator -> marciana :: 2012
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Keywordsastrodynamics
celestial mechanics
space trajectories
low-thrust
solar electric propulsion
AbstractApophis is considered by the Greeks as chaos, the God of destruction. For this reason, in current times, this name returns to scene to represent a destructive potential threat to the Earth. It is the name of an asteroid that orbits a region that represents a high risk of collision with the Earth. This asteroid was discovered in 2004 and received the initial name of 2004MN4. Then it was named Apophis, and several researchers and institutes are monitoring and designing missions with the goal of finding more information about the asteroid. The present research has the goal of finding optimal (in the sense of minimum fuel consumption) interplanetary missions, based in low thrust propulsion systems to send a spacecraft to Apophis. The spacecraft is assumed to leave the Earth from a Low Earth Orbit (LEO). An indirect optimization method is used in the simulations to find the trajectories. Two different engines will be used to determine the trajectories: the PPS1350 and the Phall 1. This is done to get some insights of the differences between a propulsion system that has a fixed magnitude for the force and one that has a magnitude that varies with the distance between the spacecraft and the Sun. Another reason to perform this research is to test the parameters of the Phall 1, that is an engine under development.
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data URLhttp://urlib.net/ibi/J8LNKAN8RW/3D5379Q
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6. Notes
Empty Fieldsalternatejournal archivist callnumber copyholder copyright creatorhistory descriptionlevel doi format isbn lineage mark mirrorrepository month nextedition notes orcid parameterlist parentrepositories previousedition previouslowerunit progress project rightsholder secondarydate session shorttitle sponsor subject targetfile tertiarymark tertiarytype typeofwork
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1. Identity statement
Reference TypeJournal Article
Siteplutao.sid.inpe.br
Holder Codeisadg {BR SPINPE} ibi 8JMKD3MGPCW/3DT298S
IdentifierJ8LNKAN8RW/3D5378P
Repositorydpi.inpe.br/plutao/2012/11.28.14.05
Last Update2013:01.16.16.06.27 (UTC) administrator
Metadata Repositorydpi.inpe.br/plutao/2012/11.28.14.05.26
Metadata Last Update2021:02.11.18.11.14 (UTC) administrator
Secondary KeyINPE--PRE/
ISSN1109-2777
Labellattes: 7340081273816424 3 AraujoWintPrad:2012:SiMuEn
Citation KeyAraujoWintPrad:2012:SiMuEn
TitleThe Swing-By Effect in the Vesta-Magnya Case. Single and Multiple Encounters
Year2012
MonthJune
Access Date2023, Jan. 31
Secondary TypePRE PI
Number of Files1
Size1578 KiB
2. Context
Author1 Araujo, Rosana Aparecida de
2 Winter, Othon Cabo
3 Prado, Antonio Fernando Bertachini de Almeida
Resume Identifier1
2
3 8JMKD3MGP5W/3C9JGJA
Group1
2
3 DMC-ETE-INPE-MCTI-GOV-BR
Affiliation1 Univ Estadual Paulista, Grupo de Dinˆamica Orbital, Guaratinguet´a, Brazil.
2 Univ Estadual Paulista, Grupo de Dinˆamica Orbital, Guaratinguet´a, Brazil.
3 Instituto Nacional de Pesquisas Espaciais (INPE)
Author e-Mail Address1
2
3 prado@dem.inpe.br
e-Mail Addressprado@dem.inpe.br
JournalWSEAS Transactions on Systems
Volume11
Number6
Pages187-197
Secondary MarkB3_ENGENHARIAS_I B3_ENGENHARIAS_III B5_ENGENHARIAS_IV C_ENSINO_DE_CIÊNCIAS_E_MATEMATICA B3_INTERDISCIPLINAR
History (UTC)2012-11-28 23:06:21 :: lattes -> marciana :: 2012
2013-01-16 16:09:01 :: marciana -> administrator :: 2012
2021-02-11 18:11:14 :: administrator -> marciana :: 2012
3. Content and structure
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KeywordsAnalytical approach
Astronomical observation
Close encounter
Energy variations
Gravity-assisted
Magnya
Orbital locations
Physical and chemical characteristics
Swing by
Vesta Engineering controlled terms: Computer applications
Systems science Engineering main heading: Asteroids
Close encounter
Magnya
Swing-by
Vesta
AbstractIt was verified that the asteroid Magnya has some physical and chemical characteristics similar to the bodies from Vesta family. However, astronomical observations revealed that Magnya is distant from these bodies. In the present work, we assumed that Magnya originated from Vesta and we try to justify its current distant orbital location taking into account the effects of close encounters between Magnya and Vesta. The methodology adopted involved an analytical approach considering the technique of the gravity assisted maneuver, also known as swing-by. We found that the energy variation achieved through a single swing-by between Vesta and Magnya are very small when compared to the variation that would be required to change the orbit of Magnya. The effects of multiple close encounters were also considered and discussed. We concluded that the possibility of multiple encounters is limited, and therefore, that Magnya should suffer other perturbations (such as resonances, collisions or close encounters with other bodies, for instance) that would provide the supposed change in its orbit.
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data URLhttp://urlib.net/ibi/J8LNKAN8RW/3D5378P
zipped data URLhttp://urlib.net/zip/J8LNKAN8RW/3D5378P
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Target File55-239.pdf
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LinkingTrabalho Vinculado à Tese/Dissertação
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URL (untrusted data)http://www.wseas.org/multimedia/journals/systems/2012/55-239.pdf
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6. Notes
Empty Fieldsalternatejournal archivist callnumber copyholder copyright creatorhistory descriptionlevel dissemination doi format isbn lineage mark mirrorrepository nextedition notes orcid parameterlist parentrepositories previousedition previouslowerunit progress project readergroup rightsholder secondarydate session shorttitle sponsor subject tertiarytype typeofwork
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1. Identity statement
Reference TypeJournal Article
Siteplutao.sid.inpe.br
Holder Codeisadg {BR SPINPE} ibi 8JMKD3MGPCW/3DT298S
IdentifierJ8LNKAN8RW/3C649BC
Repositorydpi.inpe.br/plutao/2012/06.21.21.47.25   (restricted access)
Last Update2012:08.24.17.34.41 (UTC) administrator
Metadata Repositorydpi.inpe.br/plutao/2012/06.21.21.47.26
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DOI10.1155/2012/137672
ISSN1024-123X
1563-5147
Labellattes: 3638759062433933 5 ReisSilvaZanCabForFor:2012:StStRo
Citation KeyReisSilvaZanaCabeForm:2012:StStRo
TitleStudy of Stability of Rotational Motion of Spacecraft with Canonical Variables
Year2012
Access Date2023, Jan. 31
Secondary TypePRE PI
Number of Files1
Size1071 KiB
2. Context
Author1 Reis Silva, William
2 Zanardi, Maria Cecília F. P. S.
3 Cabette, Regina Elaine Santos
4 Formiga, Jorge Kennety Silva
Group1
2
3 DMC-ETE-INPE-MCTI-GOV-BR
Affiliation1 Sao Paulo State University (UNESP) Guaratinguetá
2 Sao Paulo Salesian University (UNISAL)
3 Instituto Nacional de Pesquisas Espaciais (INPE)
4 Faculty of Technology (FATEC), Sao Jose dos Campos
Author e-Mail Address1 reis.william@gmail.com
2
3
4 jkennety@yahoo.com.br
e-Mail Addressjkennety@yahoo.com.br
JournalMathematical Problems in Engineering
Volume2012
NumberID-137672
Pages1-19
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)2012-06-22 00:11:01 :: lattes -> administrator :: 2012
2012-07-21 11:59:03 :: administrator -> secretaria.cpa@dir.inpe.br :: 2012
2012-08-24 17:34:41 :: secretaria.cpa@dir.inpe.br -> administrator :: 2012
2021-02-11 18:11:14 :: administrator -> marciana :: 2012
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AbstractThiswork aims to analyze the stability of the rotational motion of artificial satellites in circular orbit with the influence of gravity gradient torque, using the Andoyer variables. The used method in this paper to analyze stability is the Kovalev-Savchenko theorem. This method requires the reduction of the Hamiltonian in its normal form up to fourth order by means of canonical transformations around equilibrium points. The coefficients of the normal Hamiltonian are indispensable in the study of nonlinear stability of its equilibrium points according to the three established conditions in the theorem. Some physical and orbital data of real satellites were used in the numerical simulations. In comparison with previous work, the results show a greater number of equilibrium points and an optimization in the algorithm to determine the normal form and stability analysis. The results of this paper can directly contribute in maintaining the attitude of artificial satellites.
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URL (untrusted data)http://www.hindawi.com/journals/mpe/2012/137672/
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6. Notes
Empty Fieldsalternatejournal archivist callnumber copyholder copyright creatorhistory descriptionlevel format isbn keywords lineage mark mirrorrepository month nextedition notes orcid parameterlist parentrepositories previousedition previouslowerunit progress project readergroup resumeid rightsholder secondarydate secondarykey session shorttitle sponsor subject tertiarymark tertiarytype typeofwork
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1. Identity statement
Reference TypeJournal Article
Siteplutao.sid.inpe.br
Holder Codeisadg {BR SPINPE} ibi 8JMKD3MGPCW/3DT298S
IdentifierJ8LNKAN8RW/3C63NHB
Repositorydpi.inpe.br/plutao/2012/06.21.19.00   (restricted access)
Last Update2012:08.24.17.49.40 (UTC) administrator
Metadata Repositorydpi.inpe.br/plutao/2012/06.21.19.00.19
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DOI10.1016/j.applthermaleng.2011.01.017
ISSN1359-4311
Labellattes: 3396317350075844 1 RiehlSant:2012:WaNaAp
Citation KeyRiehlSant:2012:WaNaAp
TitleWater-copper nanofluid application in an open loop pulsating heat pipe
Year2012
MonthSet.
Access Date2023, Jan. 31
Secondary TypePRE PI
Number of Files1
Size649 KiB
2. Context
Author1 Riehl, Róger Ribeiro
2 Santos, Nadjara dos
Group1 DMC-ETE-INPE-MCTI-GOV-BR
Affiliation1 Instituto Nacional de Pesquisas Espaciais (INPE)
Author e-Mail Address1 rriehl@dem.inpe.br
e-Mail Addressrriehl@dem.inpe.br
JournalApplied Thermal Engineering
Volume42
Pages6-10
Secondary MarkB3_CIÊNCIA_DA_COMPUTAÇÃO B1_ENGENHARIAS_II A2_ENGENHARIAS_III B2_MEDICINA_III B3_QUÍMICA
History (UTC)2012-06-22 00:10:59 :: lattes -> administrator :: 2012
2012-07-21 07:31:35 :: administrator -> secretaria.cpa@dir.inpe.br :: 2012
2012-08-24 17:49:40 :: secretaria.cpa@dir.inpe.br -> administrator :: 2012
2012-09-30 04:31:45 :: administrator -> secretaria.cpa@dir.inpe.br :: 2012
2013-01-28 15:11:18 :: secretaria.cpa@dir.inpe.br -> administrator :: 2012
2021-02-11 18:11:12 :: administrator -> marciana :: 2012
3. Content and structure
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Keywordspulsating heat pipe
heat transfer
nanofluid
nanoparticles
AbstractSeveral investigations have pointed the operational behavior of passive thermal control devices such as loop heat pipes (LHPs) and pulsating heat pipes (PHPs) in the past, which have cleared many points related to their design. However, an interesting aspect related to passive thermal control devices that operate by means of capillary forces to pump the working fluid have gained attention during the last years, is in regard to the use of nanofluids on such devices. Nanofluids are known as regular fluids with addition of solid nanoparticles with sizes (diameter) below 40 nm, which are used to enhance the working fluid's thermal performance by enhancing its thermal conductivity. Previous works have demonstrated that the liquid's thermal conductivity can be enhanced by 20% if nanoparticles are added on a concentration of 5% by mass. PHPs operate by the dynamics of slug/plug formation, removing heat from a high temperature source and dissipating in a low temperature sink, and are highly influenced by the bubble critical diameter related to a specific working fluid. Thus, an experimental open loop PHP (OLPHP) was tested with water-copper nanofluid, with an addition of 5% by mass of copper nanoparticles. Improvements on the overall device's operation have been observed when using the nanofluid with lower temperatures, as well as a direct influence on the thermal conductances throughout the PHP. © 2011 Elsevier Ltd. All rights reserved.
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6. Notes
Empty Fieldsalternatejournal archivist callnumber copyholder copyright creatorhistory descriptionlevel format isbn lineage mark mirrorrepository nextedition notes number orcid parameterlist parentrepositories previousedition previouslowerunit progress project readergroup resumeid rightsholder secondarydate secondarykey 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/3C63KPG
Repositorydpi.inpe.br/plutao/2012/06.21.18.26.20   (restricted access)
Last Update2012:08.24.19.37.12 (UTC) administrator
Metadata Repositorydpi.inpe.br/plutao/2012/06.21.18.26.21
Metadata Last Update2021:02.11.18.11.12 (UTC) administrator
DOI10.1155/2012/905209
ISSN1024-123X
1563-5147
Labellattes: 7340081273816424 2 SukhanovPrad:2012:LoOrTr
Citation KeySukhanovPrad:2012:LoOrTr
TitleLow-Thrust Orbital Transfers in the Two-Body Problem
Year2012
Access Date2023, Jan. 31
Secondary TypePRE PI
Number of Files1
Size2225 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), RAS, Moscow, Russia
2 Instituto Nacional de Pesquisas Espaciais (INPE)
Author e-Mail Address1
2 abertachini@terra.com.br
e-Mail Addressabertachini@terra.com.br
JournalMathematical Problems in Engineering
Volume2012
NumberArticle ID 905209
Pages1-20
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)2012-06-22 00:10:59 :: lattes -> administrator :: 2012
2012-07-21 01:08:35 :: administrator -> secretaria.cpa@dir.inpe.br :: 2012
2012-11-29 13:50:22 :: secretaria.cpa@dir.inpe.br -> 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
AbstractLow-thrust transfers between given orbits within the two-body problem are considered; the thrust is assumed power limited. A simple method for obtaining the transfer trajectories based on the linearization of the motion near reference orbits is suggested. Required calculation accuracy can be reached by means of use of a proper number of the reference orbits. The method may be used in the case of a large number of the orbits around the attracting center; no averaging is necessary in this case. The suggested method also is applicable to the cases of partly given final orbit and if there are constraints on the thrust direction. The method gives an optimal solution to the linearized problem which is not optimal for the original nonlinear problem; the difference between the optimal solutions to the original and linearized problems is estimated using a numerical example. Also examples illustrating the method capacities are given.
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6. Notes
Empty Fieldsalternatejournal archivist callnumber copyholder copyright creatorhistory descriptionlevel format isbn lineage mark mirrorrepository month nextedition notes orcid parameterlist parentrepositories previousedition previouslowerunit progress project readergroup rightsholder secondarydate secondarykey 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/3C63KPD
Repositorydpi.inpe.br/plutao/2012/06.21.18.26.17   (restricted access)
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DOI10.1155/2012/493507
ISSN1024-123X
1563-5147
Labellattes: 5351862393409206 1 SantosPradCola:2012:FoReMa
Citation KeySantosPradCola:2012:FoReMa
TitleFour-Impulsive Rendezvous Maneuvers for Spacecrafts in Circular Orbits Using Genetic Algorithms
ProjectFAPESP 2009/16517-7
Year2012
Access Date2023, Jan. 31
Secondary TypePRE PI
Number of Files1
Size1078 KiB
2. Context
Author1 Santos, Denilson Paulo Souza dos
2 Prado, Antonio Fernando Bertachini de Almeida
3 Colasurdo, Guido
Resume Identifier1
2 8JMKD3MGP5W/3C9JGJA
Group1 DMC-ETE-INPE-MCTI-GOV-BR
2 DMC-ETE-INPE-MCTI-GOV-BR
Affiliation1 Instituto Nacional de Pesquisas Espaciais (INPE)
2 Instituto Nacional de Pesquisas Espaciais (INPE)
3 Department of Aerospace and Mechanical Engineering, Universit`a degli Studi di Roma “La Sapienza”
Author e-Mail Address1 denilson@dem.inpe.br
2 abertachini@terra.com.br
e-Mail Addressdenilson@dem.inpe.br
JournalMathematical Problems in Engineering
Volume2012
NumberArticle number: 493507
Pages1-16
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)2012-06-22 00:10:59 :: lattes -> administrator :: 2012
2012-07-21 12:43:19 :: administrator -> secretaria.cpa@dir.inpe.br :: 2012
2012-12-14 12:43:38 :: secretaria.cpa@dir.inpe.br -> administrator :: 2012
2021-02-11 18:11:12 :: administrator -> marciana :: 2012
3. Content and structure
Is the master or a copy?is the master
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Version Typepublisher
KeywordsCircular orbit
Engineering activities
Spacecraft maneuvers
Time-free
Algorítmos Genéticos
Manobras Orbitais
Transferências Orbitais
Swing-By
AbstractSpacecraft maneuvers is a very important topic in aerospace engineering activities today. In a more generic way, a spacecraft maneuver has the objective of transferring a spacecraft from one orbit to another, taking into account some restrictions. In the present paper, the problem of rendezvous is considered. In this type of problem, it is necessary to transfer a spacecraft from one orbit to another, but with the extra constraint of meeting another spacecraft when reaching the final orbit. In particular, the present paper aims to analyze rendezvous maneuvers between two coplanar circular orbits, seeking to perform this transfer with lowest possible fuel consumption, assuming that this problem is time-free and using four burns during the process. The assumption of four burns is used to represent a constraint posed by a real mission. Then, a genetic algorithm is used to solve the problem. After that, a study is made for a maneuver that will make a spacecraft to encounter a planet, in order to make a close approach that will change its energy. Several simulations are presented.
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6. Notes
Empty Fieldsalternatejournal archivist callnumber copyholder copyright creatorhistory descriptionlevel format isbn lineage mark mirrorrepository month nextedition notes orcid parameterlist parentrepositories previousedition previouslowerunit progress readergroup rightsholder secondarydate secondarykey 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/3C63KNP
Repositorydpi.inpe.br/plutao/2012/06.21.18.26   (restricted access)
Last Update2012:08.24.13.52.23 (UTC) administrator
Metadata Repositorydpi.inpe.br/plutao/2012/06.21.18.26.15
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DOI10.1155/2012/532708
ISSN1024-123X
1563-5147
Labellattes: 6880903376164690 1 GomesPrad:2012:LoOuOr
Citation KeyGomesPrad:2012:LoOuOr
TitleLow-Thrust Out-of-Plane Orbital Station-Keeping Maneuvers for Satellites
Year2012
Access Date2023, Jan. 31
Secondary TypePRE PI
Number of Files1
Size488 KiB
2. Context
Author1 Gomes, Vivian Martins
2 Prado, Antonio Fernando Bertachini de Almeida
Resume Identifier1
2 8JMKD3MGP5W/3C9JGJA
Group1 DMC-ETE-INPE-MCTI-GOV-BR
2 DMC-ETE-INPE-MCTI-GOV-BR
Affiliation1 Instituto Nacional de Pesquisas Espaciais (INPE)
2 Instituto Nacional de Pesquisas Espaciais (INPE)
Author e-Mail Address1 vivian.gomes@uol.com.br
2 abertachini@terra.com.br
e-Mail Addressvivian.gomes@uol.com.br
JournalMathematical Problems in Engineering
Volume2012
NumberArticle ID 532708
Pages1-14
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)2012-06-22 00:10:59 :: lattes -> administrator :: 2012
2012-07-21 12:22:07 :: administrator -> secretaria.cpa@dir.inpe.br :: 2012
2012-12-14 11:15:52 :: secretaria.cpa@dir.inpe.br -> administrator :: 2012
2021-02-11 18:11:11 :: administrator -> marciana :: 2012
3. Content and structure
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KeywordsHybrid optimal control
Low thrust
Low-thrust propulsion
Numerical results
Orbital maneuvers
Out-of plane
Small amplitude
Station-keeping
AbstractThis paper considers the problem of out of plane orbital maneuvers for station keeping of satellites. The main idea is to consider that a satellite is in an orbit around the Earth and that it has its orbit is disturbed by one or more forces. Then, it is necessary to perform a small amplitude orbital correction to return the satellite to its original orbit, to keep it performing its mission. A low thrust propulsion is used to complete this task. It is important to search for solutions that minimize the fuel consumption to increase the lifetime of the satellite. To solve this problem a hybrid optimal control approach is used. The accuracy of the satisfaction of the constraints is considered, in order to try to decrease the fuel expenditure by taking advantage of this freedom. This type of problem presents numerical difficulties and it is necessary to adjust parameters, as well as details of the algorithm, to get convergence. In this versions of the algorithm that works well for planar maneuvers are usually not adequate for the out of plane orbital corrections. In order to illustrate the method, some numerical results are presented.
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6. Notes
Empty Fieldsalternatejournal archivist callnumber copyholder copyright creatorhistory descriptionlevel format isbn lineage mark mirrorrepository month nextedition notes orcid parameterlist parentrepositories previousedition previouslowerunit progress project readergroup rightsholder secondarydate secondarykey 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/3C63E4J
Repositorydpi.inpe.br/plutao/2012/06.21.17.17.04   (restricted access)
Last Update2012:08.24.13.54.10 (UTC) administrator
Metadata Repositorydpi.inpe.br/plutao/2012/06.21.17.17.05
Metadata Last Update2021:02.11.18.11.11 (UTC) administrator
DOI10.1155/2012/740752
ISSN1024-123X
1563-5147
Labellattes: 0897606176121914 3 OliveiraKugaFons:2012:IMFaDe
Citation KeyOliveiraKugaFons:2012:IMFaDe
TitleIMU Fault Detection Based on chi(2)-CUSUM
Year2012
Access Date2023, Jan. 31
Secondary TypePRE PI
Number of Files1
Size2022 KiB
2. Context
Author1 Oliveira, Élcio Jeronimo
2 Kuga, Helio Koiti
3 Fonseca, Ijar Milagre da
Resume Identifier1
2 8JMKD3MGP5W/3C9JHC9
3 8JMKD3MGP5W/3C9JHD8
Group1
2 DMC-ETE-INPE-MCTI-GOV-BR
3 DMC-ETE-INPE-MCTI-GOV-BR
Affiliation1 Space Systems Division, Institute of Aeronautics and Space (IAE), 12.228-904 São José dos Campos, SP, Brazil
2 Instituto Nacional de Pesquisas Espaciais (INPE)
3 Instituto Nacional de Pesquisas Espaciais (INPE)
Author e-Mail Address1
2 hkk@dem.inpe.br
3 ijar@dem.inpe.br
e-Mail Addressijar@dem.inpe.br
JournalMathematical Problems in Engineering
Volume2012
NumberArticle ID 740752
Pages1-15
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)2012-06-22 00:10:59 :: lattes -> administrator :: 2012
2012-07-21 11:30:42 :: administrator -> secretaria.cpa@dir.inpe.br :: 2012
2012-12-14 12:14:28 :: secretaria.cpa@dir.inpe.br -> administrator :: 2012
2021-02-11 18:11:11 :: administrator -> marciana :: 2012
3. Content and structure
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Content TypeExternal Contribution
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Keywordsfault detection and Isolation
IMU
Fiber optical gyros
chi-square cumulative sum
AbstractThe problem of fault detection and isolation (FDI) on inertial measurement units (IMUs) has received great attention in the last years, mainly with growing use of IMU strapdown platforms using fiber optic gyros (FOG) or micro electro mechanical systems (MEMSs). A way to solve this problem makes use of sensor redundancy and parity vector (PV) analysis. However, the actual sensor outputs can include some anomalies, as impulsive noise which can be associated with the sensors itself or data acquisition process, committing the elementary threshold criteria as commonly used. Therefore, to overcome this problem, in this work, it is proposed an algorithm based on median filter (MF) for prefiltering and chi-square cumulative sum ( 2 -CUSUM) only for fault detection (FD) applied to an IMU composed by four FOGs. Copyright © 2012 lcio Jeronimo de Oliveira et al.
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6. Notes
Empty Fieldsalternatejournal archivist callnumber copyholder copyright creatorhistory descriptionlevel format isbn lineage mark mirrorrepository month nextedition notes orcid parameterlist parentrepositories previousedition previouslowerunit progress project readergroup rightsholder secondarydate secondarykey 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/3C63E4E
Repositorydpi.inpe.br/plutao/2012/06.21.17.17   (restricted access)
Last Update2012:08.24.12.16.57 (UTC) administrator
Metadata Repositorydpi.inpe.br/plutao/2012/06.21.17.17.01
Metadata Last Update2021:02.11.18.11.11 (UTC) administrator
DOI10.1155/2012/596396
ISSN1024-123X
1563-5147
Labellattes: 1786255724025154 2 BaroniKuga:2012:AnAtDe
Citation KeyBaroniKuga:2012:AnAtDe
TitleAnalysis of Attitude Determination Methods Using GPS Carrier Phase Measurements
Year2012
Access Date2023, Jan. 31
Secondary TypePRE PI
Number of Files1
Size1871 KiB
2. Context
Author1 Baroni, Leandro
2 Kuga, Hélio Koiti
Resume Identifier1
2 8JMKD3MGP5W/3C9JHC9
Group1
2 DMC-ETE-INPE-MCTI-GOV-BR
Affiliation1 Institute of Science, Engineering and Technology, Federal University of Jequitinhonha and Mucuri Valleys (UFVJM)
2 Instituto Nacional de Pesquisas Espaciais (INPE)
Author e-Mail Address1
2 hkk@dem.inpe.br
e-Mail Addresshkk@dem.inpe.br
JournalMathematical Problems in Engineering
Volume2012
NumberArticle number: 596396
Pages1-10
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)2012-06-22 00:10:59 :: lattes -> administrator :: 2012
2012-07-21 01:11:22 :: administrator -> secretaria.cpa@dir.inpe.br :: 2012
2012-12-14 10:49:14 :: secretaria.cpa@dir.inpe.br -> administrator :: 2012
2021-02-11 18:11:11 :: administrator -> marciana :: 2012
3. Content and structure
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KeywordsAttitude Determination
GPS ambiguity resolution
Lambda method
LSAST method
AbstractIf three or more GPS antennas are mounted properly on a platform and differences of GPS signals measurements are collected simultaneously, the baselines vectors between antennas can be determined and the platform orientation defined by these vectors can be calculated. Thus, the prerequisite for attitude determination technique based on GPS is to calculate baselines between antennas to millimeter level of accuracy. For accurate attitude solutions to be attained, carrier phase double differences are used as main type of measurements. The use of carrier phase measurements leads to the problem of precise determination of the ambiguous integer number of cycles in the initial carrier phase integer ambiguity. In this work two algorithms LSAST and LAMBDA were implemented and tested for ambiguity resolution allowing accurate real-time attitude determination using measurements given by GPS receivers in coupled form. Platform orientation was obtained using quaternions formulation, and the results showed that LSAST method performance is similar to LAMBDA as far as the number of epochs which are necessary to resolve ambiguities is concerned, but with processing time significantly higher. The final result accuracy was similar for both methods, better than 0.1. to 0.2., when baselines are considered in decoupled form.
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6. Notes
NotesSetores de Atividade: Pesquisa e desenvolvimento científico.
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