Enhanced attitude control structure for small satellites with reaction wheels

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Enhanced attitude control structure for small satellites with reaction wheels

Ismail, Zuliana / Varatharajoo, Renuganth / Ajir, Ramly / Mohd Rafie, Azmin Shakrine

– 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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Document information

Title :

Enhanced attitude control structure for small satellites with reaction wheels

Contributors:

Renuganth Varatharajoo, Prof (editor) / Ismail, Zuliana (author) / Varatharajoo, Renuganth (author) / Ajir, Ramly (author) / Mohd Rafie, Azmin Shakrine (author)

Published in:

Aircraft Engineering and Aerospace Technology: An International Journal ; 87 , 6 ; 546-550

Publication date :

2015-10-05

Size :

5 pages

ISSN :

0002-2667

DOI :

https://doi.org/10.1108/AEAT-06-2014-0085

Type of media :

Article (Journal)