Enhanced attitude control structure for small satellites with reaction wheels
Purpose: This paper aims to describe a design enhancement for the satellite attitude control system using reaction wheels, and the wheel momentum unloading using magnetorquers. Design/methodology/approach: The proportional – integral–derivative-controller and active force control (AFC) schemes are d...
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Main Authors: | , , , |
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Format: | Article |
Language: | English |
Published: |
Emerald
2015
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Online Access: | http://psasir.upm.edu.my/id/eprint/44624/1/Enhanced%20attitude%20control%20structure%20for%20small%20satellites%20with%20reaction%20wheels.pdf http://psasir.upm.edu.my/id/eprint/44624/ https://www.emerald.com/insight/content/doi/10.1108/AEAT-06-2014-0085/full/html |
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Summary: | Purpose: This paper aims to describe a design enhancement for the satellite attitude control system using reaction wheels, and the wheel momentum unloading using magnetorquers. Design/methodology/approach: The proportional – integral–derivative-controller and active force control (AFC) schemes are developed together with their governing equations for closed loop system of attitude control. Four numerical simulations were carried out using the Matlab – Simulink™ software and results were compared. Findings: From the results, it is evident that the attitude accuracies for roll–pitch–yaw axes have improved significantly through the proportional – derivative (PD) – AFC controller for the attitude control and the wheel momentum can be well maintained during the momentum unloading scheme. The results show that the AFC has a high potential to be implemented in the satellite attitude control system. Practical implications: Using AFC, the actual disturbance torque is considered totally rejected by the system without having to have any direct prior knowledge on the actual disturbance itself. Originality/value: The results demonstrate the satellite attitude control using reaction wheel is enhanced by PD–AFC attitude controller. |
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