Magnetic attitude control for nano-satellites
The active magnetic attitude control technique is a recognized attitude control option for small satellites operated in Low Earth Orbit (LEO). The purpose of this thesis is to control a nano-satellite that is operated in LEO so that it always pointing toward the Earth. Two options of control algorit...
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my-utm-ep.485222017-07-13T01:13:39Z Magnetic attitude control for nano-satellites 2014 Ibrahim, Syahrim Azhan TL Motor vehicles. Aeronautics. Astronautics The active magnetic attitude control technique is a recognized attitude control option for small satellites operated in Low Earth Orbit (LEO). The purpose of this thesis is to control a nano-satellite that is operated in LEO so that it always pointing toward the Earth. Two options of control algorithms have been considered for a gravity-gradient satellite. The first control is a passive type, structured for the gravity-gradient satellite (Satellite A). It relies totally on the orbited body's mass distribution and gravitational field. The second control is an active type, structured for the gravity-gradient satellite employing three magnetic torquers onboard (Satellite B). The control is accomplished using a set of magnetic torquers that can generate a mechanical torque thus producing control actions when the torquers interact with the geomagnetic field. The algorithm used in Satellite B is configured for controlling roll, pitch and yaw attitudes using a proportional-derivative (PD) controller. Both control algorithms are simulated using the MATLAB®/ SIMULINK® software. The control algorithms were tested using a simplified geomagnetic model for a reference space mission. Their attitude performances were compared and it is found that both controls fulfil the mission requirements. However, the system in satellite B gives a better attitude performance. Specifically, the roll axis oscillates between -2.4° and 3.2° while the pitch axis oscillates between -2.4° and 2.0°. Finally, the yaw axis swing is much controllable with an oscillation between -1.7° and 0.4°. This work provides us an insight when designing a real magnetic attitude control subsystem for nano-satellites. 2014 Thesis http://eprints.utm.my/id/eprint/48522/ http://eprints.utm.my/id/eprint/48522/1/SyahrimAzhanBinIbrahimMFKE2014.pdf application/pdf en public http://dms.library.utm.my:8080/vital/access/manager/Repository/vital:86098?queryType=vitalDismax&query=Magnetic+attitude+control+for+nano-satellites&public=true masters Universiti Teknologi Malaysia, Faculty of Electrical Engineering Faculty of Electrical Engineering |
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TL Motor vehicles Aeronautics Astronautics |
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TL Motor vehicles Aeronautics Astronautics Ibrahim, Syahrim Azhan Magnetic attitude control for nano-satellites |
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The active magnetic attitude control technique is a recognized attitude control option for small satellites operated in Low Earth Orbit (LEO). The purpose of this thesis is to control a nano-satellite that is operated in LEO so that it always pointing toward the Earth. Two options of control algorithms have been considered for a gravity-gradient satellite. The first control is a passive type, structured for the gravity-gradient satellite (Satellite A). It relies totally on the orbited body's mass distribution and gravitational field. The second control is an active type, structured for the gravity-gradient satellite employing three magnetic torquers onboard (Satellite B). The control is accomplished using a set of magnetic torquers that can generate a mechanical torque thus producing control actions when the torquers interact with the geomagnetic field. The algorithm used in Satellite B is configured for controlling roll, pitch and yaw attitudes using a proportional-derivative (PD) controller. Both control algorithms are simulated using the MATLAB®/ SIMULINK® software. The control algorithms were tested using a simplified geomagnetic model for a reference space mission. Their attitude performances were compared and it is found that both controls fulfil the mission requirements. However, the system in satellite B gives a better attitude performance. Specifically, the roll axis oscillates between -2.4° and 3.2° while the pitch axis oscillates between -2.4° and 2.0°. Finally, the yaw axis swing is much controllable with an oscillation between -1.7° and 0.4°. This work provides us an insight when designing a real magnetic attitude control subsystem for nano-satellites. |
format |
Thesis |
qualification_level |
Master's degree |
author |
Ibrahim, Syahrim Azhan |
author_facet |
Ibrahim, Syahrim Azhan |
author_sort |
Ibrahim, Syahrim Azhan |
title |
Magnetic attitude control for nano-satellites |
title_short |
Magnetic attitude control for nano-satellites |
title_full |
Magnetic attitude control for nano-satellites |
title_fullStr |
Magnetic attitude control for nano-satellites |
title_full_unstemmed |
Magnetic attitude control for nano-satellites |
title_sort |
magnetic attitude control for nano-satellites |
granting_institution |
Universiti Teknologi Malaysia, Faculty of Electrical Engineering |
granting_department |
Faculty of Electrical Engineering |
publishDate |
2014 |
url |
http://eprints.utm.my/id/eprint/48522/1/SyahrimAzhanBinIbrahimMFKE2014.pdf |
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1747817410941943808 |