Attitude control simulation of small satellites with reaction wheels

Nowadays, most of the designed satellites are dedicated for high performance missions, which require high attitude pointing accuracies. The reaction wheel is the most suitable satellite actuator that can provide high attitude pointing accuracies (0.1°-0.001°). Commonly, three or four reaction wheel...

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Main Author:	Ismail, Zuliana
Format:	Thesis
Language:	English
Published:	2009
Subjects:	Remote Sensing/Photogrammetry Remote sensing Astronautics
Online Access:	http://psasir.upm.edu.my/id/eprint/51549/1/FK%202009%20119RR.pdf
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id	my-upm-ir.51549
record_format	uketd_dc
spelling	my-upm-ir.515492017-03-30T04:39:48Z Attitude control simulation of small satellites with reaction wheels 2009-12 Ismail, Zuliana Nowadays, most of the designed satellites are dedicated for high performance missions, which require high attitude pointing accuracies. The reaction wheel is the most suitable satellite actuator that can provide high attitude pointing accuracies (0.1°-0.001°). Commonly, three or four reaction wheel configurations are used for a 3-axis satellite attitude control. In fact, higher power is consumed when multiple reaction wheels are employed. Thus, it is rather challenging to adopt multiple reaction wheels for the small satellite missions because of the power constraint. On the other hand, reaction wheels lack of the ability to remove the excess angular momentum and that the wheels have a limited capacity to store momentum. Without a momentum management control, the satellite may be uncontrollable. Therefore, to make the implementation of multiple reaction wheels reliable for a small satellite, it is necessary to find a way to minimize the wheel’s power consumption. Also, it is compulsory for a satellite to be equipped with a momentum management scheme in order to maintain the angular momentum within their allowable limits. Momentum management control using magnetic torquers are chosen in this work. Indeed, the wheel’s power consumption can be lowered by particularly arranging the reaction wheels’ orientation onboard the satellite. In this research, several configurations, based on three or four reaction wheels, are investigated in order to identify the most suitable orientation with the total minimum power. All the related mathematical models are implemented in Matlab-SimulinkTM software. Numerical simulations are performed for all the possible reaction wheel configurations with respect to an identical reference mission. Two simulation analyses are presented for their performance evaluations. First simulation focuses on the satellite attitude control only and the second simulation focuses on the satellite attitude control with momentum management control. Based on the simulations, the reaction wheel configuration that produces a minimum total control torque is identified, which also corresponds to the configuration with a minimum power intake. The wheel angular momentums and satellite attitude accuracies are also well maintained during the control task. Remote Sensing/Photogrammetry Remote sensing Astronautics 2009-12 Thesis http://psasir.upm.edu.my/id/eprint/51549/ http://psasir.upm.edu.my/id/eprint/51549/1/FK%202009%20119RR.pdf application/pdf en public masters Universiti Putra Malaysia Remote Sensing/Photogrammetry Remote sensing Astronautics
institution	Universiti Putra Malaysia
collection	PSAS Institutional Repository
language	English
topic	Remote Sensing/Photogrammetry Remote sensing Astronautics
spellingShingle	Remote Sensing/Photogrammetry Remote sensing Astronautics Ismail, Zuliana Attitude control simulation of small satellites with reaction wheels
description	Nowadays, most of the designed satellites are dedicated for high performance missions, which require high attitude pointing accuracies. The reaction wheel is the most suitable satellite actuator that can provide high attitude pointing accuracies (0.1°-0.001°). Commonly, three or four reaction wheel configurations are used for a 3-axis satellite attitude control. In fact, higher power is consumed when multiple reaction wheels are employed. Thus, it is rather challenging to adopt multiple reaction wheels for the small satellite missions because of the power constraint. On the other hand, reaction wheels lack of the ability to remove the excess angular momentum and that the wheels have a limited capacity to store momentum. Without a momentum management control, the satellite may be uncontrollable. Therefore, to make the implementation of multiple reaction wheels reliable for a small satellite, it is necessary to find a way to minimize the wheel’s power consumption. Also, it is compulsory for a satellite to be equipped with a momentum management scheme in order to maintain the angular momentum within their allowable limits. Momentum management control using magnetic torquers are chosen in this work. Indeed, the wheel’s power consumption can be lowered by particularly arranging the reaction wheels’ orientation onboard the satellite. In this research, several configurations, based on three or four reaction wheels, are investigated in order to identify the most suitable orientation with the total minimum power. All the related mathematical models are implemented in Matlab-SimulinkTM software. Numerical simulations are performed for all the possible reaction wheel configurations with respect to an identical reference mission. Two simulation analyses are presented for their performance evaluations. First simulation focuses on the satellite attitude control only and the second simulation focuses on the satellite attitude control with momentum management control. Based on the simulations, the reaction wheel configuration that produces a minimum total control torque is identified, which also corresponds to the configuration with a minimum power intake. The wheel angular momentums and satellite attitude accuracies are also well maintained during the control task.
format	Thesis
qualification_level	Master's degree
author	Ismail, Zuliana
author_facet	Ismail, Zuliana
author_sort	Ismail, Zuliana
title	Attitude control simulation of small satellites with reaction wheels
title_short	Attitude control simulation of small satellites with reaction wheels
title_full	Attitude control simulation of small satellites with reaction wheels
title_fullStr	Attitude control simulation of small satellites with reaction wheels
title_full_unstemmed	Attitude control simulation of small satellites with reaction wheels
title_sort	attitude control simulation of small satellites with reaction wheels
granting_institution	Universiti Putra Malaysia
publishDate	2009
url	http://psasir.upm.edu.my/id/eprint/51549/1/FK%202009%20119RR.pdf
_version_	1747812062526963712

Attitude control simulation of small satellites with reaction wheels

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