| 1. Identity statement | ||||
| Reference Type | Journal Article | |||
| Site | mtc-m21b.sid.inpe.br | |||
| Holder Code | isadg {BR SPINPE} ibi 8JMKD3MGPCW/3DT298S | |||
| Identifier | 8JMKD3MGP3W34P/3PFBJUL | |||
| Repository | sid.inpe.br/mtc-m21b/2017/08.18.18.30 (restricted access) | |||
| Last Update | 2017:08.18.18.30.18 (UTC) administrator | |||
| Metadata Repository | sid.inpe.br/mtc-m21b/2017/08.18.18.30.18 | |||
| Metadata Last Update | 2021:02.11.18.12.43 (UTC) administrator | |||
| DOI | 10.1016/j.actaastro.2017.07.018 | |||
| ISSN | 0094-5765 | |||
| Citation Key | FonsecaRadeGoesSale:2017:AtViCo | |||
| Title | Attitude and vibration control of a satellite containing flexible solar arrays by using reaction wheels, and piezoelectric transducers as sensors and actuators  | |||
| Year | 2017 | |||
| Month | Oct. | |||
| Access Date | 2024, May 19 | |||
| Type of Work | journal article | |||
| Secondary Type | PRE PI | |||
| Number of Files | 1 | |||
| Size | 2984 KiB | |||
| 2. Context | ||||
| Author | 1 Fonseca, Ijar Milagre da 2 Rade, Domingos A. 3 Goes, Luiz C. S. 4 Sales, Thiago de Paula | |||
| Resume Identifier | 1 8JMKD3MGP5W/3C9JHD8 | |||
| Group | 1 DIDMC-CGETE-INPE-MCTIC-GOV-BR | |||
| Affiliation | 1 Instituto Nacional de Pesquisas Espaciais (INPE) 2 Instituto Tecnológico de Aeronáutica (ITA) 3 Instituto Tecnológico de Aeronáutica (ITA) 4 Universidade Federal de Uberlândia (UFU) | |||
| Author e-Mail Address | 1 ijar@uol.com.br | |||
| Journal | Acta Astronautica | |||
| Volume | 139 | |||
| Pages | 357-366 | |||
| Secondary Mark | A2_INTERDISCIPLINAR B1_GEOCIÊNCIAS B1_ENGENHARIAS_IV B1_ENGENHARIAS_III B2_CIÊNCIA_DA_COMPUTAÇÃO C_ENGENHARIAS_II C_ASTRONOMIA_/_FÍSICA | |||
| History (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. Content and structure | ||||
| Is the master or a copy? | is the master | |||
| Content Stage | completed | |||
| Transferable | 1 | |||
| Content Type | External Contribution | |||
| Version Type | publisher | |||
| Abstract | The 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. | |||
| Area | ETES | |||
| Arrangement | urlib.net > BDMCI > Fonds > Produção anterior à 2021 > DIDMC > Attitude and vibration... | |||
| doc Directory Content | access | |||
| source Directory Content | there are no files | |||
| agreement Directory Content |
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| 4. Conditions of access and use | ||||
| Language | en | |||
| Target File | fonseca_attitude.pdf | |||
| User Group | simone | |||
| Reader Group | administrator simone | |||
| Visibility | shown | |||
| Archiving Policy | denypublisher denyfinaldraft24 | |||
| Read Permission | deny from all and allow from 150.163 | |||
| Update Permission | not transferred | |||
| 5. Allied materials | ||||
| Next Higher Units | 8JMKD3MGPCW/446AF4B | |||
| Citing Item List | sid.inpe.br/bibdigital/2021/02.11.18.06 3 | |||
| Dissemination | WEBSCI; PORTALCAPES; COMPENDEX. | |||
| Host Collection | sid.inpe.br/mtc-m21b/2013/09.26.14.25.20 | |||
| 6. Notes | ||||
| Empty Fields | alternatejournal 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. Description control | ||||
| e-Mail (login) | simone | |||
| update | ||||