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9 referências encontradas buscando em 15 dentre 15 sites.
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Tipo da ReferênciaJournal Article
Identificador8JMKD3MGP3W/3HG7CLE
Repositóriosid.inpe.br/plutao/2014/12.01.12.07.51   (acesso restrito)
Metadadossid.inpe.br/plutao/2014/12.01.12.07.52
Siteplutao.sid.inpe.br
Rótulolattes: 0288494962313241 1 CarraraOlivKuga:2014:GaBePl
ISSN0065-3438
Código do Detentorisadg {BR SPINPE} ibi 8JMKD3MGPCW/3DT298S
Chave de CitaçãoCarraraOlivKuga:2014:GaBePl
Autor1 Carrara, Valdemir
2 Oliveira, Alexandre Macedo de
3 Kuga, Helio Koiti
Identificador de Curriculo1 8JMKD3MGP5W/3C9JJAN
2
3 8JMKD3MGP5W/3C9JHC9
Grupo1 DMC-ETE-INPE-MCTI-GOV-BR
2
3 DMC-ETE-INPE-MCTI-GOV-BR
Afiliação1 Instituto Nacional de Pesquisas Espaciais (INPE)
2
3 Instituto Nacional de Pesquisas Espaciais (INPE)
Endereço de e-Mail do Autor1 val@dem.inpe.br
2
3 helio.kuga@inpe.br
TítuloA gas bearing platform attitude control for assessment of AOCS systems
RevistaAdvances in the Astronautical Sciences
Ano2014
Volume152
Número1
Palavras-Chaveair bearing, Attitude control, Attitude dynamics, Extended Kalman Filter.
ResumoThis paper presents a solution for the development, validation and testing of attitude control system for satellites with hardware-in-the-loop dynamics and control. The system is based on a gas-bearing platform in which several sensors and actuators, similar to those usually employed in satellites (engineering models) were fixed. Magnetometers and gyroscopes are easily incorporated to the platform, but sun sensors and star sensors are more difficult. The solar sensors are replaced by a tri-axes accelerometer, while the star sensor relies on direct night sky measurements. Although hot gas thrusters cannot be used, both magnetic torque coils and reaction wheels are feasible to be incorporated to the arrangement. The gas-bearing balancing process is critical for real satellite dynamic simulation and therefore the solution is addressed in this work, by means of a non-linear filtering of the sensor readings. The filtering process also obtains the platform mass properties. In order to increase the filter accuracy the gyroscopes were calibrated; the calibration results are also presented here. Finally, an attitude controller was implemented in the platform and the control performance was analyzed and shown together with the conclusions.
Páginas2677-2695
NotasSetores de Atividade: Pesquisa e desenvolvimento científico.
Idiomaen
Tipo SecundárioPRE PI
DivulgaçãoWEBSCI; PORTALCAPES; COMPENDEX; SCOPUS.
AreaETES
Nota TerciáriaTrabalho não Vinculado à Tese/Dissertação
Tamanho896 KiB
Número de Arquivos1
Arquivo AlvoCarrara_Gas.pdf
Última Atualização2015:02.11.16.52.53 dpi.inpe.br/plutao@80/2008/08.19.15.01 administrator
Última Atualização dos Metadados2018:06.04.23.39.35 dpi.inpe.br/plutao@80/2008/08.19.15.01 administrator {D 2014}
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Endereço de e-Mailmarcelo.pazos@inpe.br
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Acervo Hospedeirodpi.inpe.br/plutao@80/2008/08.19.15.01
Tipo do ConteudoExternal Contribution
Estágio do Documentonot transferred
Tipo de Versãopublisher
Política de Arquivamentodenypublisher denyfinaldraft
Permissão de Leituradeny from all and allow from 150.163
Conteúdo da Pasta sourcenão têm arquivos
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Histórico2014-12-01 12:07:52 :: lattes -> administrator ::
2018-06-04 23:39:35 :: administrator -> marcelo.pazos@inpe.br :: 2014
Campos Vaziosalternatejournal archivist callnumber copyholder copyright creatorhistory descriptionlevel doi format isbn lineage mark month nextedition nexthigherunit orcid parameterlist parentrepositories previousedition previouslowerunit progress project rightsholder secondarydate secondarykey secondarymark session shorttitle sponsor subject tertiarytype typeofwork url
Data de Acesso23 out. 2020
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Tipo da ReferênciaJournal Article
Identificador8JMKD3MGP5W34M/3GD3H67
Repositóriosid.inpe.br/mtc-m21b/2014/05.30.02.29.29
Metadadossid.inpe.br/mtc-m21b/2014/05.30.02.29.30
Sitemtc-m21b.sid.inpe.br
DOI10.1093/mnras/stt2040
Rótuloisi 2014-05 CarrubaDomHuaSanSou:2014:DyEvCh
ISSN0035-8711
Código do Detentorisadg {BR SPINPE} ibi 8JMKD3MGPCW/3DT298S
Chave de CitaçãoCarrubaDomHuaSanSou:2014:DyEvCh
Autor1 Carruba, V.
2 Domingos, R. C.
3 Huaman, M. E.
4 Santos, C. R. dos
5 Souami, D.
Grupo1
2 DMC-ETE-INPE-MCTI-GOV-BR
Afiliação1 Universidade Estadual Paulista (UNESP)
2 Instituto Nacional de Pesquisas Espaciais (INPE)
3 Universidade Estadual Paulista (UNESP)
4 Universidade Estadual Paulista (UNESP)
5 University of Namur
Endereço de e-Mail do Autor1 vcarruba@feg.unesp.br
TítuloDynamical evolution and chronology of the Hygiea asteroid family
RevistaMonthly Notices of the Royal Astronomical Society
Ano2014
Volume437
Número3
MêsJan.
Palavras-Chavecelestial mechanics, minor planets, asteroids: general, minor planets, asteroids: individual: Hygiea.
ResumoThe asteroid (10) Hygiea is the fourth largest asteroid of the main belt, by volume and mass, and it is the largest member of its own family. Previous works investigated the long-term effects of close encounters with (10) Hygiea of asteroids in the orbital region of the family, and analysed the taxonomical and dynamical properties of members of this family. In this paper we apply the high-quality Sloan Digital Sky Survey-Moving Object Catalog data, fourth release (SDSS-MOC4) taxonomic scheme of DeMeo & Carry to members of the Hygiea family core and halo, we obtain an estimate of the minimum time and number of encounter necessary to obtain a 3 sigma (or 99.7 per cent) compatible frequency distribution function of changes in proper a caused by close encounters with (10) Hygiea, we study the behaviour of asteroids near secular resonance configurations, in the presence and absence of the Yarkovsky force, and obtain a first estimate of the age of the family based on orbital diffusion by the Yarkovsky and Yarkovsky-O'Keefe-Radzievsky-Paddack (YORP) effects with two methods. The Hygiea family is at least 2 Byr old, with an estimated age of T = 3200(-120)(+380) Myr and a relatively large initial ejection velocity field, according to the approach of Vokrouhlicky et al. Surprisingly, we found that the family age can be shortened by similar or equal to 25 per cent if the dynamical mobility caused by close encounters with (10) Hygiea is also accounted for, which opens interesting new research lines for the dynamical evolution of families associated with massive bodies. In our taxonomical analysis of the Hygiea asteroid family, we also identified a new V-type candidate: the asteroid (177904) (2005 SV5). If confirmed, this could be the fourth V-type object ever to be identified in the outer main belt.
Páginas2279-2290
Idiomaen
Tipo de Trabalhojournal article
Tipo SecundárioPRE PI
DivulgaçãoWEBSCI; PORTALCAPES; SCOPUS.
AreaETES
Projeto(FAPESP) that supported this work via the grant 11/19863-3, and the Brazilian National Research Council (CNPq, grant 305453/2011-4).
Nota SecundáriaA1_ENGENHARIAS_III A1_QUÍMICA A1_GEOCIÊNCIAS A1_INTERDISCIPLINAR A2_ASTRONOMIA_/_FÍSICA A2_MATEMÁTICA_/_PROBABILIDADE_E B2_ENSINO B5_ENGENHARIAS_IV
Tamanho1858 KiB
Número de Arquivos1
Arquivo AlvoMNRAS-2014-Carruba-2279-90.pdf
Última Atualização2014:07.29.17.19.59 sid.inpe.br/mtc-m21b/2013/09.26.14.25.20 administrator
Última Atualização dos Metadados2018:06.04.03.04.18 sid.inpe.br/mtc-m21b/2013/09.26.14.25.20 administrator {D 2014}
Estágio do Documentoconcluido
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Espelhoiconet.com.br/banon/2006/11.26.21.31
Endereço de e-Mailmarcelo.pazos@inpe.br
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Acervo Hospedeirosid.inpe.br/mtc-m21b/2013/09.26.14.25.20
Tipo do ConteudoExternal Contribution
Estágio do Documentonot transferred
Tipo de Versãopublisher
Política de Arquivamentoallowpublisher allowfinaldraft
Unidades Imediatamente Superiores8JMKD3MGPCW/3EU29DP
Conteúdo da Pasta sourcenão têm arquivos
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Histórico2018-06-04 03:04:18 :: administrator -> marcelo.pazos@inpe.br :: 2014
Campos Vaziosalternatejournal archivist callnumber copyholder copyright creatorhistory descriptionlevel format isbn lineage mark nextedition notes orcid parameterlist parentrepositories previousedition previouslowerunit progress readpermission resumeid rightsholder secondarydate secondarykey session shorttitle sponsor subject tertiarymark tertiarytype url
Data de Acesso23 out. 2020
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Tipo da ReferênciaJournal Article
Identificador8JMKD3MGP5W34M/3GD3GC6
Repositóriosid.inpe.br/mtc-m21b/2014/05.30.02.20.01
Metadadossid.inpe.br/mtc-m21b/2014/05.30.02.20.02
Sitemtc-m21b.sid.inpe.br
DOI10.1093/mnras/stu192
Rótuloscopus 2014-05 CarrubaHuaDomDosSou:2014:DyEvVt
ISSN0035-8711
Código do Detentorisadg {BR SPINPE} ibi 8JMKD3MGPCW/3DT298S
Chave de CitaçãoCarrubaHuaDomSanSou:2014:DyEvVt
Autor1 Carruba, V.
2 Huaman, M. E.
3 Domingos, R. C.
4 Santos, C. R. dos
5 Souami, D.
Grupo1
2
3 DMC-ETE-INPE-MCTI-GOV-BR
Afiliação1 UNESP, Univ. Estadual Paulista, Grupo de dinâmica Orbital e Planetologia, Guaratinguetá, SP 12516-410, Brazil
2 UNESP, Univ. Estadual Paulista, Grupo de dinâmica Orbital e Planetologia, Guaratinguetá, SP 12516-410, Brazil
3 Instituto Nacional de Pesquisas Espaciais (INPE)
4 UNESP, Univ. Estadual Paulista, Grupo de dinâmica Orbital e Planetologia, Guaratinguetá, SP 12516-410, Brazil
5 NAXYS, Namur Center for Complex Systems, Department of Mathematics, University of Namur, B-5000 Namur, Belgium; UPMC, Université Pierre et Marie Curie, 4 Place Jussieu, F-75005 Paris, France; SYRTE, Observatoire de Paris, Systèmes de Référence Temps Espace, CNRS/UMR 8630, UPMC, Paris, France
Endereço de e-Mail do Autor1 vcarruba@feg.unesp.br
TítuloDynamical evolution of V-type asteroids in the central main belt
RevistaMonthly Notices of the Royal Astronomical Society
Ano2014
Volume439
Número3
Palavras-Chavecelestial mechanics, minor planets, asteroids.
ResumoV-type asteroids are associated with basaltic composition, and are supposed to be fragments of crust of differentiated objects. Most V-type asteroids in the main belt are found in the inner main belt, and are either current members of the Vesta dynamical family (Vestoids), or past members that drifted away. However, several V-type photometric candidates have been recently identified in the central and outer main belt. The origin of this large population of V-type objects is not well understood. Since it seems unlikely that Vestoids crossing the 3J:-1A mean-motion resonance with Jupiter could account for the whole population of V-type asteroids in the central and outer main belt, origin from local sources, such as the parent bodies of the Eunomia, and of the Merxia and Agnia asteroid families, has been proposed as an alternative mechanism. In this work, we investigated the dynamical evolution of the V-type photometric candidates in the central main belt, under the effect of gravitational and non-gravitational forces. Our results showthat dynamical evolution from the parent bodies of the Eunomia and Merxia/Agnia families on time-scales of 2 Byr or more could be responsible for the current orbital location of most of the low-inclined V-type asteroids.
Páginas3168-3179
Idiomaen
Tipo de Trabalhojournal article
Tipo SecundárioPRE PI
DivulgaçãoWEBSCI; PORTALCAPES; SCOPUS.
AreaETES
Nota SecundáriaA1_ENGENHARIAS_III A1_QUÍMICA A1_GEOCIÊNCIAS A1_INTERDISCIPLINAR A2_ASTRONOMIA_/_FÍSICA A2_MATEMÁTICA_/_PROBABILIDADE_E B2_ENSINO B5_ENGENHARIAS_IV
Tamanho3443 KiB
Número de Arquivos1
Arquivo AlvoMNRAS-2014-Carruba-mnras_stu192.pdf
Última Atualização2014:07.29.17.50.02 sid.inpe.br/mtc-m21b/2013/09.26.14.25.20 administrator
Última Atualização dos Metadados2018:06.04.03.04.11 sid.inpe.br/mtc-m21b/2013/09.26.14.25.20 administrator {D 2014}
Estágio do Documentoconcluido
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Endereço de e-Mailmarcelo.pazos@inpe.br
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Visibilidadeshown
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Acervo Hospedeirosid.inpe.br/mtc-m21b/2013/09.26.14.25.20
Tipo do ConteudoExternal Contribution
Estágio do Documentonot transferred
Tipo de Versãopublisher
Política de Arquivamentoallowpublisher allowfinaldraft
Unidades Imediatamente Superiores8JMKD3MGPCW/3F2NE4L
Conteúdo da Pasta sourcenão têm arquivos
Conteúdo da Pasta agreementnão têm arquivos
Histórico2018-06-04 03:04:11 :: administrator -> marcelo.pazos@inpe.br :: 2014
Campos Vaziosalternatejournal archivist callnumber copyholder copyright creatorhistory descriptionlevel format isbn lineage mark month nextedition notes orcid parameterlist parentrepositories previousedition previouslowerunit progress project readpermission resumeid rightsholder secondarydate secondarykey session shorttitle sponsor subject tertiarymark tertiarytype url
Data de Acesso23 out. 2020
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similares 
Tipo da ReferênciaJournal Article
Identificador8JMKD3MGP5W34M/3HE6FH5
Repositóriosid.inpe.br/mtc-m21b/2014/11.19.00.00.03   (acesso restrito)
Metadadossid.inpe.br/mtc-m21b/2014/11.19.00.00.04
Sitemtc-m21b.sid.inpe.br
DOI10.1155/2014/529716
Rótuloscopus 2014-11 CarvalhoVilhPrad:2014:SeLePe
ISSN1024-123X
Código do Detentorisadg {BR SPINPE} ibi 8JMKD3MGPCW/3DT298S
Chave de CitaçãoCarvalhoVilhPrad:2014:SeLePe
Autor1 Carvalho, J. P. S.
2 Vilhena De Moraes, R.
3 Prado, Antonio Fernando Bertachini de Almeida
Identificador de Curriculo1
2
3 8JMKD3MGP5W/3C9JGJA
Grupo1
2
3 DMC-ETE-INPE-MCTI-GOV-BR
Afiliação1 Universidade Federal de São Paulo (UNIFESP)
2 Universidade Federal de São Paulo (UNIFESP)
3 Instituto Nacional de Pesquisas Espaciais (INPE)
Endereço de e-Mail do Autor1 jeanfeg@gmail.com
2
3 antonio.prado@inpe.br
TítuloSearching less perturbed circular orbits for a spacecraft travelling around Europa
RevistaMathematical Problems in Engineering
Ano2014
Volume2014
Palavras-ChaveGravitation, Interplanetary flight, Satellites, Circular orbit, Dynamical model, Gravitational potential, Natural satellites, Orbital element, Perturbing forces, Space activities, Third-body perturbations, Orbits.
ResumoSpace missions to visit the natural satellite of Jupiter, Europa, constitute an important topic in space activities today, because missions to this moon are under study now. Several considerations have to be made for these missions. The present paper searches for less perturbed circular orbits around Europa. This search is made based on the total effects of the perturbing forces over the time, evaluated by the integral of those forces over the time. This value depends on the dynamical model and on the orbit of the spacecraft. The perturbing forces considered are the third-body perturbation that comes from Jupiter and the J 2, J 3, and C 22 terms of the gravitational potential of Europa. Several numerical studies are performed and the results show the locations of the less perturbed orbits. Using those results, it is possible to find near-circular frozen orbits with smaller amplitudes of variations of the orbital elements.
Idiomaen
Tipo de Trabalhojournal article
Tipo SecundárioPRE PI
DivulgaçãoWEBSCI; PORTALCAPES; SCOPUS.
AreaETES
Nota SecundáriaA2_ENGENHARIAS_I B1_INTERDISCIPLINAR B1_ENGENHARIAS_III B1_ENGENHARIAS_IV B1_GEOCIÊNCIAS B1_CIÊNCIAS_AGRÁRIAS_I B2_ENGENHARIAS_II B3_CIÊNCIA_DA_COMPUTAÇÃO B4_MATEMÁTICA_/_PROBABILIDADE_E B4_CIÊNCIAS_BIOLÓGICAS_II B5_ASTRONOMIA_/_FÍSICA
Nota TerciáriaTrabalho não Vinculado à Tese/Dissertação
Tamanho3756 KiB
Número de Arquivos1
Arquivo AlvoCarvalho_searching.pdf
Última Atualização2015:02.11.16.28.57 sid.inpe.br/mtc-m21b/2013/09.26.14.25.20 administrator
Última Atualização dos Metadados2018:06.04.03.04.33 sid.inpe.br/mtc-m21b/2013/09.26.14.25.20 administrator {D 2014}
Estágio do Documentoconcluido
É a matriz ou uma cópia?é a matriz
Espelhoiconet.com.br/banon/2006/11.26.21.31
Endereço de e-Mailmarcelo.pazos@inpe.br
e-Mail (login)marcelo.pazos@inpe.br
Grupo de Usuáriosadministrator
marcelo.pazos@inpe.br
Grupo de Leitoresadministrator
marcelo.pazos@inpe.br
Visibilidadeshown
Transferível1
Acervo Hospedeirosid.inpe.br/mtc-m21b/2013/09.26.14.25.20
Tipo do ConteudoExternal Contribution
Estágio do Documentonot transferred
Tipo de Versãopublisher
Política de Arquivamentodenypublisher allowfinaldraft
Permissão de Leituradeny from all and allow from 150.163
Conteúdo da Pasta sourcenão têm arquivos
Conteúdo da Pasta agreementnão têm arquivos
Histórico2018-06-04 03:04:33 :: administrator -> marcelo.pazos@inpe.br :: 2014
Campos Vaziosalternatejournal archivist callnumber copyholder copyright creatorhistory descriptionlevel format isbn lineage mark month nextedition nexthigherunit notes number orcid pages parameterlist parentrepositories previousedition previouslowerunit progress project rightsholder secondarydate secondarykey session shorttitle sponsor subject tertiarytype url
Data de Acesso23 out. 2020
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similares 
Tipo da ReferênciaJournal Article
Identificador8JMKD3MGP5W34M/3HE6FBR
Repositóriosid.inpe.br/mtc-m21b/2014/11.18.23.57.41   (acesso restrito)
Metadadossid.inpe.br/mtc-m21b/2014/11.18.23.57.42
Sitemtc-m21b.sid.inpe.br
DOI10.1155/2014/359845
Rótuloscopus 2014-11 DomingosPradGome:2014:EfEcPe
ISSN1024-123X
Código do Detentorisadg {BR SPINPE} ibi 8JMKD3MGPCW/3DT298S
Chave de CitaçãoDomingosPradGome:2014:EfEcPe
Autor1 Domingos, R. C.
2 Prado, Antonio Fernando Bertachini de Almeida
3 Gomes, V. M.
Identificador de Curriculo1
2 8JMKD3MGP5W/3C9JGJA
Grupo1
2 DMC-ETE-INPE-MCTI-GOV-BR
Afiliação1 Universidade Estadual Paulista (UNESP)
2 Instituto Nacional de Pesquisas Espaciais (INPE)
3 Universidade Estadual Paulista (UNESP)
Endereço de e-Mail do Autor1
2 antonio.prado@inpe.br
TítuloEffects of the eccentricity of a perturbing third body on the orbital correction maneuvers of a spacecraft
RevistaMathematical Problems in Engineering
Ano2014
Volume2014
Palavras-ChaveSpacecraft, Annual cost, Averaged models, Dwarf planets, Eccentric orbits, Orbital maneuvers, Planetary system, Station keeping, Three-body problem, Orbits.
ResumoThe fuel consumption required by the orbital maneuvers when correcting perturbations on the orbit of a spacecraft due to a perturbing body was estimated. The main goals are the measurement of the influence of the eccentricity of the perturbing body on the fuel consumption required by the station keeping maneuvers and the validation of the averaged methods when applied to the problem of predicting orbital maneuvers. To study the evolution of the orbits, the restricted elliptic three-body problem and the single- and double-averaged models are used. Maneuvers are made by using impulsive and low thrust maneuvers. The results indicated that the averaged models are good to make predictions for the orbital maneuvers when the spacecraft is in a high inclined orbit. The eccentricity of the perturbing body plays an important role in increasing the effects of the perturbation and the fuel consumption required for the station keeping maneuvers. It is shown that the use of more frequent maneuvers decreases the annual cost of the station keeping to correct the orbit of a spacecraft. An example of an eccentric planetary system of importance to apply the present study is the dwarf planet Haumea and its moons, one of them in an eccentric orbit.
Idiomaen
Tipo de Trabalhojournal article
Tipo SecundárioPRE PI
DivulgaçãoWEBSCI; PORTALCAPES; SCOPUS.
AreaETES
Nota SecundáriaA2_ENGENHARIAS_I B1_INTERDISCIPLINAR B1_ENGENHARIAS_III B1_ENGENHARIAS_IV B1_GEOCIÊNCIAS B1_CIÊNCIAS_AGRÁRIAS_I B2_ENGENHARIAS_II B3_CIÊNCIA_DA_COMPUTAÇÃO B4_MATEMÁTICA_/_PROBABILIDADE_E B4_CIÊNCIAS_BIOLÓGICAS_II B5_ASTRONOMIA_/_FÍSICA
Nota TerciáriaTrabalho não Vinculado à Tese/Dissertação
Tamanho2425 KiB
Número de Arquivos1
Arquivo AlvoDomingos_effects.pdf
Última Atualização2015:02.11.15.37.19 sid.inpe.br/mtc-m21b/2013/09.26.14.25.20 administrator
Última Atualização dos Metadados2018:06.04.03.04.30 sid.inpe.br/mtc-m21b/2013/09.26.14.25.20 administrator {D 2014}
Estágio do Documentoconcluido
É a matriz ou uma cópia?é a matriz
Espelhoiconet.com.br/banon/2006/11.26.21.31
Endereço de e-Mailmarcelo.pazos@inpe.br
e-Mail (login)marcelo.pazos@inpe.br
Grupo de Usuáriosadministrator
marcelo.pazos@inpe.br
Grupo de Leitoresadministrator
marcelo.pazos@inpe.br
Visibilidadeshown
Transferível1
Acervo Hospedeirosid.inpe.br/mtc-m21b/2013/09.26.14.25.20
Tipo do ConteudoExternal Contribution
Estágio do Documentonot transferred
Tipo de Versãopublisher
Política de Arquivamentodenypublisher allowfinaldraft
Permissão de Leituradeny from all and allow from 150.163
Conteúdo da Pasta sourcenão têm arquivos
Conteúdo da Pasta agreementnão têm arquivos
Histórico2018-06-04 03:04:30 :: administrator -> marcelo.pazos@inpe.br :: 2014
Campos Vaziosalternatejournal archivist callnumber copyholder copyright creatorhistory descriptionlevel format isbn lineage mark month nextedition nexthigherunit notes number orcid pages parameterlist parentrepositories previousedition previouslowerunit progress project rightsholder secondarydate secondarykey session shorttitle sponsor subject tertiarytype url
Data de Acesso23 out. 2020
atualizar 
similares 
Tipo da ReferênciaJournal Article
Identificador8JMKD3MGP5W34M/3GD3GFU
Repositóriosid.inpe.br/mtc-m21b/2014/05.30.02.21.44
Metadadossid.inpe.br/mtc-m21b/2014/05.30.02.21.45
Sitemtc-m21b.sid.inpe.br
DOI10.1088/0004-637X/784/1/22
Rótuloscopus 2014-05 NesvornýVokrDeie:2014:CaIrSa
ISSN0004-637X
1538-4357
Código do Detentorisadg {BR SPINPE} ibi 8JMKD3MGPCW/3DT298S
Chave de CitaçãoNesvornýVokrDeie:2014:CaIrSa
Autor1 Nesvorný, David
2 Vokrouhlický, David
3 Deienno, Rogerio
Grupo1
2
3 DMC-ETE-INPE-MCTI-GOV-BR
Afiliação1 Department of Space Studies, Southwest Research Institute, 1050 Walnut Street, Boulder, CO 80302, United States
2 Department of Space Studies, Southwest Research Institute, 1050 Walnut Street, Boulder, CO 80302, United States; Institute of Astronomy, Charles University, V Holeaovi kách 2, 18000 Prague 8, Czech Republic
3 Instituto Nacional de Pesquisas Espaciais (INPE)
TítuloCapture of irregular satellites at jupiter
RevistaAstrophysical Journal
Ano2014
Volume784
Número1
MêsMar.
Palavras-Chaveplanets, satellites, formation.
ResumoThe irregular satellites of outer planets are thought to have been captured from heliocentric orbits. The exact nature of the capture process, however, remains uncertain. We examine the possibility that irregular satellites were captured from the planetesimal disk during the early solar system instability when encounters between the outer planets occurred. Nesvorný et al. already showed that the irregular satellites of Saturn, Uranus, and Neptune were plausibly captured during planetary encounters. Here we find that the current instability models present favorable conditions for capture of irregular satellites at Jupiter as well, mainly because Jupiter undergoes a phase of close encounters with an ice giant. We show that the orbital distribution of bodies captured during planetary encounters provides a good match to the observed distribution of irregular satellites at Jupiter. The capture efficiency for each particle in the original transplanetary disk is found to be (1.3-3.6) × 10-8. This is roughly enough to explain the observed population of jovian irregular moons. We also confirm Nesvorný et al.'s results for the irregular satellites of Saturn, Uranus, and Neptune.
Páginas6pp
Idiomaen
Tipo de Trabalhojournal article
Tipo SecundárioPRE PI
DivulgaçãoWEBSCI; PORTALCAPES; COMPENDEX; SCOPUS.
AreaETES
ProjetoFAPESP (2012/23732; 2010/11109).
Tamanho531 KiB
Número de Arquivos1
Arquivo Alvo0004-637X_784_1_22.pdf
Última Atualização2014:07.15.17.15.42 sid.inpe.br/mtc-m21b/2013/09.26.14.25.20 administrator
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Campos Vaziosalternatejournal archivist callnumber copyholder copyright creatorhistory descriptionlevel electronicmailaddress format isbn lineage mark nextedition nexthigherunit notes orcid parameterlist parentrepositories previousedition previouslowerunit progress resumeid rightsholder secondarydate secondarykey secondarymark session shorttitle sponsor subject tertiarymark tertiarytype url
Data de Acesso23 out. 2020
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Tipo da ReferênciaJournal Article
Identificador8JMKD3MGP5W34M/3HE6FJF
Repositóriosid.inpe.br/mtc-m21b/2014/11.19.00.00.40   (acesso restrito)
Metadadossid.inpe.br/mtc-m21b/2014/11.19.00.00.41
Sitemtc-m21b.sid.inpe.br
DOI10.1155/2014/678015
Rótuloscopus 2014-11 PardalMoraKuga:2014:EfGeAt
ISSN1024-123X
Código do Detentorisadg {BR SPINPE} ibi 8JMKD3MGPCW/3DT298S
Chave de CitaçãoPardalMoraKuga:2014:EfGeAt
Autor1 Pardal, P. C. P. M.
2 Moraes, R. V. De
3 Kuga, Hélio Koiti
Identificador de Curriculo1
2
3 8JMKD3MGP5W/3C9JHC9
Grupo1
2
3 DMC-ETE-INPE-MCTI-GOV-BR
Afiliação1 Universidade de São Paulo (USP)
2 Universidade Federal de São Paulo (UNIFESP)
3 Instituto Nacional de Pesquisas Espaciais (INPE)
TítuloEffects of geopotential and atmospheric drag effects on frozen orbits using nonsingular variables
RevistaMathematical Problems in Engineering
Ano2014
Volume2014
Palavras-ChaveDrag, Satellites, Analytical expressions, Argument of perigees, Atmospheric drag, China-brazil earth resources satellites, Classical equation, Non-singular variables, Orbital evolutions, System of nonlinear differential equations, Orbits.
ResumoThe concept of frozen orbit has been applied in space missions mainly for orbital tracking and control purposes. This type of orbit is important for orbit design because it is characterized by keeping the argument of perigee and eccentricity constant on average, so that, for a given latitude, the satellite always passes at the same altitude, benefiting the users through this regularity. Here, the system of nonlinear differential equations describing the motion is studied, and the effects of geopotential and atmospheric drag perturbations on frozen orbits are taken into account. Explicit analytical expressions for secular and long period perturbations terms are obtained for the eccentricity and the argument of perigee. The classical equations of Brouwer and Brouwer and Hori theories are used. Nonsingular variables approach is used, which allows obtaining more precise previsions for CBERS (China Brazil Earth Resources Satellite) satellites family and similar satellites (SPOT, Landsat, ERS, and IRS) orbital evolution. © 2014 Paula Cristiane Pinto Mesquita Pardal et al.
Idiomaen
Tipo de Trabalhojournal article
Tipo SecundárioPRE PI
DivulgaçãoWEBSCI; PORTALCAPES; SCOPUS.
AreaETES
Nota SecundáriaA2_ENGENHARIAS_I B1_INTERDISCIPLINAR B1_ENGENHARIAS_III B1_ENGENHARIAS_IV B1_GEOCIÊNCIAS B1_CIÊNCIAS_AGRÁRIAS_I B2_ENGENHARIAS_II B3_CIÊNCIA_DA_COMPUTAÇÃO B4_MATEMÁTICA_/_PROBABILIDADE_E B4_CIÊNCIAS_BIOLÓGICAS_II B5_ASTRONOMIA_/_FÍSICA
Nota TerciáriaTrabalho não Vinculado à Tese/Dissertação
Tamanho2680 KiB
Número de Arquivos1
Última Atualização2015:02.10.14.03.55 sid.inpe.br/mtc-m21b/2013/09.26.14.25.20 administrator
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Estágio do Documentonot transferred
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Política de Arquivamentodenypublisher allowfinaldraft
Permissão de Leituradeny from all and allow from 150.163
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Histórico2018-06-04 03:04:33 :: administrator -> marcelo.pazos@inpe.br :: 2014
Campos Vaziosalternatejournal archivist callnumber copyholder copyright creatorhistory descriptionlevel electronicmailaddress format isbn lineage mark month nextedition nexthigherunit notes number orcid pages parameterlist parentrepositories previousedition previouslowerunit progress project rightsholder secondarydate secondarykey session shorttitle sponsor subject targetfile tertiarytype url
Data de Acesso23 out. 2020
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Tipo da ReferênciaJournal Article
Identificador8JMKD3MGP5W34M/3GD3GGT
Repositóriosid.inpe.br/mtc-m21b/2014/05.30.02.22.10   (acesso restrito)
Metadadossid.inpe.br/mtc-m21b/2014/05.30.02.22.11
Sitemtc-m21b.sid.inpe.br
DOI10.1016/j.asr.2013.12.034
Rótuloscopus 2014-05 Prado:2014:MaOrAr
ISSN0273-1177 1879-1948
Código do Detentorisadg {BR SPINPE} ibi 8JMKD3MGPCW/3DT298S
Chave de CitaçãoPrado:2014:MaOrAr
AutorPrado, Antonio Fernando Bertachini de Almeida
Identificador de Curriculo8JMKD3MGP5W/3C9JGJA
GrupoDMC-ETE-INPE-MCTI-GOV-BR
AfiliaçãoInstituto Nacional de Pesquisas Espaciais (INPE)
Endereço de e-Mail do Autorprado@dem.inpe.br
TítuloMapping orbits around the asteroid 2001SN263
RevistaAdvances in Space Research
Ano2014
Volume53
Número5
MêsMar.
Palavras-Chaveastrodynamics, orbital perturbations, third-body effects, oblateness effects, orbital maneuvers.
ResumoThe present paper has the goal of mapping orbits, with respect to the perturbations, for a spacecraft traveling around the asteroid 2001SN 263. This asteroid is a triple system, which center of mass is in an elliptic orbit around the Sun. The perturbations considered in the present model are the ones due to the oblateness of the central body, the gravity field of the two satellite bodies (Beta and Gamma), the Sun, the Moon, the asteroids Vesta, Pallas and Ceres and all the planets of the Solar System. This mapping is important, because it shows the relative importance of each force for a given orbit for the spacecraft, helping to make a decision about which forces need to be included in the model for a given accuracy and nominal orbit. Another important application of this type of mapping is to find orbits that are less perturbed, since it is expected that those orbits have good potential to require a smaller number of station-keeping maneuvers. Simulations under different conditions are made to find those orbits. The main reason to study those trajectories is that, currently, there are several institutions in Brazil studying the possibility to make a mission to send a spacecraft to this asteroid (the so-called ASTER mission), because there are many important scientific studies that can be performed in that system. The results showed that Gamma is the main perturbing body, followed by Beta (10 times smaller) and the group Sun-Mars-oblateness of Alpha, with perturbations 1000 times weaker than the effects of Gamma. The other bodies have perturbations 107 times smaller. The results also showed that circular and polar orbits are less perturbed, when compared to elliptical and equatorial orbits. Regarding the semi-major axis, an internal orbit is the best choice, followed by a larger external orbit. The inclination of the orbit plays an important role, and there are values for the inclination where the perturbations show minimum and maximum values, so it is important to make a good decision on those values.
Páginas877-889
Idiomaen
URL (dados não confiáveis)http://dx.doi.org/10.1016/j.asr.2013.12.034
Tipo de Trabalhojournal article
Tipo SecundárioPRE PI
DivulgaçãoWEBSCI; PORTALCAPES; COMPENDEX; SCOPUS.
AreaETES
ProjetoCNPq (473387/2012-3; 304700/2009-6), FAPESP (2011/09310-7; 2011/08171-3).
Tamanho1171 KiB
Número de Arquivos1
Arquivo Alvo1-s2.0-S0273117713008314-main.pdf
Última Atualização2014:07.16.14.23.24 sid.inpe.br/mtc-m21b/2013/09.26.14.25.20 administrator
Última Atualização dos Metadados2018:06.04.03.04.13 sid.inpe.br/mtc-m21b/2013/09.26.14.25.20 administrator {D 2014}
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Acervo Hospedeirosid.inpe.br/mtc-m21b/2013/09.26.14.25.20
Tipo do ConteudoExternal Contribution
Estágio do Documentonot transferred
Tipo de Versãopublisher
Política de Arquivamentodenypublisher denyfinaldraft24
Permissão de Leituradeny from all and allow from 150.163
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Histórico2018-06-04 03:04:13 :: administrator -> marcelo.pazos@inpe.br :: 2014
Campos Vaziosalternatejournal archivist callnumber copyholder copyright creatorhistory descriptionlevel format isbn lineage mark nextedition nexthigherunit notes orcid parameterlist parentrepositories previousedition previouslowerunit progress rightsholder secondarydate secondarykey secondarymark session shorttitle sponsor subject tertiarymark tertiarytype
Data de Acesso23 out. 2020
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Tipo da ReferênciaJournal Article
Identificador8JMKD3MGP5W34M/3HE6FC6
Repositóriosid.inpe.br/mtc-m21b/2014/11.18.23.57.49   (acesso restrito)
Metadadossid.inpe.br/mtc-m21b/2014/11.18.23.57.50
Sitemtc-m21b.sid.inpe.br
DOI10.1155/2014/260206
Rótuloscopus 2014-11 SouzaSouz:2014:SaAtCo
ISSN1070-9622
Código do Detentorisadg {BR SPINPE} ibi 8JMKD3MGPCW/3DT298S
Chave de CitaçãoSouzaSouz:2014:SaAtCo
Autor1 Souza, Luiz Carlos Gadelha de
2 Souza, Alain Giacobini De
Identificador de Curriculo1 8JMKD3MGP5W/3C9JHN3
Grupo1 DMC-ETE-INPE-MCTI-GOV-BR
2 CMC-ETES-SPG-INPE-MCTI-GOV-BR
Afiliação1 Instituto Nacional de Pesquisas Espaciais (INPE)
2 Instituto Nacional de Pesquisas Espaciais (INPE)
TítuloSatellite attitude control system design considering the fuel slosh dynamics
RevistaShock and Vibration
Ano2014
Volume2014
Palavras-ChaveCommunication satellites, Controllers, Design, Dynamics, Fuel tanks, Navigation, Controller performance, Flexible solar panels, Kalman filter technique, Linear quadratic Gaussian, Linear quadratic regulator, Mechanical manipulators, Satellite attitude control systems, Satellite structure, Satellite antennas.
ResumoThe design of the satellite attitude control system (ACS) becomes more complex when the satellite structure has different type of components like, flexible solar panels, antennas, mechanical manipulators, and tanks with fuel. A crucial interaction can occur between the fuel slosh motion and the satellite rigid motion during translational and/or rotational manoeuvre since these interactions can change the satellite centre of mass position damaging the ACS pointing accuracy. Although, a well-designed controller can suppress such disturbances quickly, the controller error pointing may be limited by the minimum time necessary to suppress such disturbances thus affecting the satellite attitude acquisition. As a result, the design of the satellite controller needs to explore the limits between the conflicting requirements of performance and robustness. This paper investigates the effects of the interaction between the liquid motion (slosh) and the satellite dynamics in order to predict what the damage to the controller performance and robustness is. The fuel slosh dynamics is modelled by a pendulum which parameters are identified using the Kalman filter technique. This information is used to design the satellite controller by the linear quadratic regulator (LQR) and linear quadratic Gaussian (LQG) methods to perform a planar manoeuvre assuming thrusters are actuators. © 2014 Luiz Carlos Gadelha de Souza and Alain G. de Souza.
Idiomaen
Tipo SecundárioPRE PI
DivulgaçãoWEBSCI; PORTALCAPES; COMPENDEX; SCOPUS.
AreaETES
Nota SecundáriaB1_INTERDISCIPLINAR B1_ENGENHARIAS_III B1_ENGENHARIAS_I B2_ENGENHARIAS_IV
Nota TerciáriaTrabalho não Vinculado à Tese/Dissertação
Tamanho2548 KiB
Número de Arquivos1
Última Atualização2015:02.09.11.59.53 sid.inpe.br/mtc-m21b/2013/09.26.14.25.20 administrator
Última Atualização dos Metadados2018:06.04.03.04.30 sid.inpe.br/mtc-m21b/2013/09.26.14.25.20 administrator {D 2014}
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Data de Acesso23 out. 2020
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