Enhanced attitude control structure for small satellites with reaction wheels

• Main Authors: Ismail, Zuliana, Varatharajoo, Renuganth, Mohd Ajir, Mohd Ramly, Mohd Rafie, Azmin Shakrine
• Format: Article
• Language: English
• Published: Emerald 2015
• 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

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.