Satellite Attitude Control Using Control Moment Gyroscopes
In space missions, there is often a need for an attitude control system capable of maintaining the desired attitude. In situations that require agile and accurate responses, which also require large torques, control moment gyroscopes (CMGs) may be used. Control moment gyroscopes are high angular mom...
| Main Authors: | , , , , , , , |
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| Format: | Article |
| Language: | English |
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Instituto de Aeronáutica e Espaço (IAE)
2020-11-01
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| Series: | Journal of Aerospace Technology and Management |
| Subjects: | |
| Online Access: | http://www.jatm.com.br/ojs/index.php/jatm/article/view/1156/866 |
| _version_ | 1828521556985249792 |
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| author | Kenedy Matiasso Portella Wilcker Neuwald Schinestzki Róger Mateus Sehnem Leonardo Barros da Luz Lorenzzo Quevedo Mantovani Renan Rathis Sacco Tarso Kraemer Sarzi Sartori Pedro Paglione |
| author_facet | Kenedy Matiasso Portella Wilcker Neuwald Schinestzki Róger Mateus Sehnem Leonardo Barros da Luz Lorenzzo Quevedo Mantovani Renan Rathis Sacco Tarso Kraemer Sarzi Sartori Pedro Paglione |
| author_sort | Kenedy Matiasso Portella |
| collection | DOAJ |
| description | In space missions, there is often a need for an attitude control system capable of maintaining the desired attitude. In situations that require agile and accurate responses, which also require large torques, control moment gyroscopes (CMGs) may be used. Control moment gyroscopes are high angular moment gyros mounted on gimbals and are responsible for changing the direction of the angular momentum vector, consequently generating the control torques. There are several linear and nonlinear techniques that can be employed in the design of control laws with the final choice being a compromise between simplicity, effectiveness, efficiency and robustness. The main objective of this study is to evaluate the performance of control systems techniques with 4 CMGs in a pyramidal arrangement, either by using Linear Quadratic Tracker (LQT) with integral compensator or Exponential
Mapping Control (EMC). A reference attitude will be defined to be traced in the presence of disturbance torques caused by the gravitational gradient. |
| first_indexed | 2024-12-11T19:50:49Z |
| format | Article |
| id | doaj.art-a1155912b1f84c85ac5f4304e9b77d24 |
| institution | Directory Open Access Journal |
| issn | 1984-9648 2175-9146 |
| language | English |
| last_indexed | 2024-12-11T19:50:49Z |
| publishDate | 2020-11-01 |
| publisher | Instituto de Aeronáutica e Espaço (IAE) |
| record_format | Article |
| series | Journal of Aerospace Technology and Management |
| spelling | doaj.art-a1155912b1f84c85ac5f4304e9b77d242022-12-22T00:52:46ZengInstituto de Aeronáutica e Espaço (IAE)Journal of Aerospace Technology and Management1984-96482175-91462020-11-0112se94105http://dx.doi.org/10.5028/jatm.cab.1156Satellite Attitude Control Using Control Moment GyroscopesKenedy Matiasso Portella0 Wilcker Neuwald Schinestzki1Róger Mateus Sehnem2 Leonardo Barros da Luz3 Lorenzzo Quevedo Mantovani4Renan Rathis Sacco 5Tarso Kraemer Sarzi Sartori6Pedro Paglione7Institut Polytechnique de Grenoble Universidade Federal de Santa Maria Universidade Federal de Santa Maria Universidade Federal de Santa Maria Universidade Federal de Santa Maria Universidade Federal de Santa Maria Universidade Federal de Santa Maria Universidade Federal de Santa Maria In space missions, there is often a need for an attitude control system capable of maintaining the desired attitude. In situations that require agile and accurate responses, which also require large torques, control moment gyroscopes (CMGs) may be used. Control moment gyroscopes are high angular moment gyros mounted on gimbals and are responsible for changing the direction of the angular momentum vector, consequently generating the control torques. There are several linear and nonlinear techniques that can be employed in the design of control laws with the final choice being a compromise between simplicity, effectiveness, efficiency and robustness. The main objective of this study is to evaluate the performance of control systems techniques with 4 CMGs in a pyramidal arrangement, either by using Linear Quadratic Tracker (LQT) with integral compensator or Exponential Mapping Control (EMC). A reference attitude will be defined to be traced in the presence of disturbance torques caused by the gravitational gradient.http://www.jatm.com.br/ojs/index.php/jatm/article/view/1156/866control moment gyroscopeslinear quadratic trackerexponential mapping controlnonlinear controlattitude control |
| spellingShingle | Kenedy Matiasso Portella Wilcker Neuwald Schinestzki Róger Mateus Sehnem Leonardo Barros da Luz Lorenzzo Quevedo Mantovani Renan Rathis Sacco Tarso Kraemer Sarzi Sartori Pedro Paglione Satellite Attitude Control Using Control Moment Gyroscopes Journal of Aerospace Technology and Management control moment gyroscopes linear quadratic tracker exponential mapping control nonlinear control attitude control |
| title | Satellite Attitude Control Using Control Moment Gyroscopes |
| title_full | Satellite Attitude Control Using Control Moment Gyroscopes |
| title_fullStr | Satellite Attitude Control Using Control Moment Gyroscopes |
| title_full_unstemmed | Satellite Attitude Control Using Control Moment Gyroscopes |
| title_short | Satellite Attitude Control Using Control Moment Gyroscopes |
| title_sort | satellite attitude control using control moment gyroscopes |
| topic | control moment gyroscopes linear quadratic tracker exponential mapping control nonlinear control attitude control |
| url | http://www.jatm.com.br/ojs/index.php/jatm/article/view/1156/866 |
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