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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Main Author:	Ibrahim, Syahrim Azhan
Format:	Thesis
Language:	English
Published:	2014
Subjects:	TL Motor vehicles Aeronautics Astronautics
Online Access:	http://eprints.utm.my/id/eprint/48522/1/SyahrimAzhanBinIbrahimMFKE2014.pdf
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id	my-utm-ep.48522
record_format	uketd_dc
spelling	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
institution	Universiti Teknologi Malaysia
collection	UTM Institutional Repository
language	English
topic	TL Motor vehicles Aeronautics Astronautics
spellingShingle	TL Motor vehicles Aeronautics Astronautics Ibrahim, Syahrim Azhan Magnetic attitude control for nano-satellites
description	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
_version_	1747817410941943808

Magnetic attitude control for nano-satellites

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