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Metadados

1. Identificação
Tipo de ReferênciaArtigo em Revista Científica (Journal Article)
Sitemtc-m21b.sid.inpe.br
Código do Detentorisadg {BR SPINPE} ibi 8JMKD3MGPCW/3DT298S
Identificador8JMKD3MGP3W34P/3PFBJUL
Repositóriosid.inpe.br/mtc-m21b/2017/08.18.18.30   (acesso restrito)
Última Atualização2017:08.18.18.30.18 (UTC) administrator
Repositório de Metadadossid.inpe.br/mtc-m21b/2017/08.18.18.30.18
Última Atualização dos Metadados2021:02.11.18.12.43 (UTC) administrator
DOI10.1016/j.actaastro.2017.07.018
ISSN0094-5765
Chave de CitaçãoFonsecaRadeGoesSale:2017:AtViCo
TítuloAttitude and vibration control of a satellite containing flexible solar arrays by using reaction wheels, and piezoelectric transducers as sensors and actuators
Ano2017
MêsOct.
Data de Acesso20 maio 2024
Tipo de Trabalhojournal article
Tipo SecundárioPRE PI
Número de Arquivos1
Tamanho2984 KiB
2. Contextualização
Autor1 Fonseca, Ijar Milagre da
2 Rade, Domingos A.
3 Goes, Luiz C. S.
4 Sales, Thiago de Paula
Identificador de Curriculo1 8JMKD3MGP5W/3C9JHD8
Grupo1 DIDMC-CGETE-INPE-MCTIC-GOV-BR
Afiliação1 Instituto Nacional de Pesquisas Espaciais (INPE)
2 Instituto Tecnológico de Aeronáutica (ITA)
3 Instituto Tecnológico de Aeronáutica (ITA)
4 Universidade Federal de Uberlândia (UFU)
Endereço de e-Mail do Autor1 ijar@uol.com.br
RevistaActa Astronautica
Volume139
Páginas357-366
Nota SecundáriaA2_INTERDISCIPLINAR B1_GEOCIÊNCIAS B1_ENGENHARIAS_IV B1_ENGENHARIAS_III B2_CIÊNCIA_DA_COMPUTAÇÃO C_ENGENHARIAS_II C_ASTRONOMIA_/_FÍSICA
Histórico (UTC)2017-08-18 18:30:18 :: simone -> administrator ::
2017-08-18 18:30:18 :: administrator -> simone :: 2017
2017-08-18 18:31:15 :: simone -> administrator :: 2017
2021-02-11 18:12:43 :: administrator -> simone :: 2017
3. Conteúdo e estrutura
É a matriz ou uma cópia?é a matriz
Estágio do Conteúdoconcluido
Transferível1
Tipo do ConteúdoExternal Contribution
Tipo de Versãopublisher
ResumoThe primary purpose of this paper is to provide insight into control-structure interaction for satellites comprising flexible appendages and internal moving components. The physical model considered herein aiming to attend such purpose is a rigid-flexible satellite consisting of a rigid platform containing two rotating flexible solar panels. The solar panels rotation is assumed to be in a sun-synchronous configuration mode. The panels contain surface-bonded piezoelectric patches that can be used either as sensors for the elastic displacements or as actuators to counteract the vibration motion. It is assumed that in the normal mode operation the satellite platform points towards the Earth while the solar arrays rotate so as to follow the Sun. The vehicle moves in a low Earth polar orbit. The technique used to obtain the mathematical model combines the Lagrangian formulation with the Finite Elements Method used to describe the dynamics of the solar panel. The gravity-gradient torque as well as the torque due to the interaction of the Earth magnetic field and the satellite internal residual magnetic moment is included as environmental perturbations. The actuators are three reaction wheels for attitude control and piezoelectric actuators to control the flexible motion of the solar arrays. Computer simulations are performed using the MATLAB® software package. The following on-orbit satellite operating configurations are object of analysis: i) Satellite pointing towards the Earth (Earth acquisition maneuver) by considering the initial conditions in the elastic displacement equal to zero, aiming the assessment of the flexible modes excitation by the referred maneuver; ii) the satellite pointing towards the Earth with the assumption of an initial condition different from zero for the flexible motion such that the attitude alterations are checked against the elastic motion disturbance; and iii) attitude acquisition accomplished by taking into account initial conditions different from zero for both attitude and elastic vibrations. Additionally, the control efforts for the three cases are compared. Results indicate that the attitude control is able to excite the solar panels' vibration modes and vice-versa. The piezoelectric vibration control shows significant performance improvement when compared to contributions of the attitude control to the vibration damping.
ÁreaETES
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Conteúdo da Pasta docacessar
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Conteúdo da Pasta agreement
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4. Condições de acesso e uso
Idiomaen
Arquivo Alvofonseca_attitude.pdf
Grupo de Usuáriossimone
Grupo de Leitoresadministrator
simone
Visibilidadeshown
Política de Arquivamentodenypublisher denyfinaldraft24
Permissão de Leituradeny from all and allow from 150.163
Permissão de Atualizaçãonão transferida
5. Fontes relacionadas
Unidades Imediatamente Superiores8JMKD3MGPCW/446AF4B
Lista de Itens Citandosid.inpe.br/bibdigital/2021/02.11.18.06 3
DivulgaçãoWEBSCI; PORTALCAPES; COMPENDEX.
Acervo Hospedeirosid.inpe.br/mtc-m21b/2013/09.26.14.25.20
6. Notas
Campos Vaziosalternatejournal archivist callnumber copyholder copyright creatorhistory descriptionlevel e-mailaddress format isbn keywords label lineage mark mirrorrepository nextedition notes number orcid parameterlist parentrepositories previousedition previouslowerunit progress project rightsholder schedulinginformation secondarydate secondarykey session shorttitle sponsor subject tertiarymark tertiarytype url
7. Controle da descrição
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