Affiliation:
1. Universiti Sains Malaysia
Abstract
In this paper, a three-axis attitude control of a small satellite employing control moment gyroscope (CMG) is presented. A four single gimbal control moment gyroscopes (4-SGCMG) cluster has been employed as the actuator and a proportional-derivative (PD) based attitude control approach has been utilized. The singularity robust (SR) steering law has been employed to investigate its capability in avoiding the singularity state of the CMG system with respect to the mission operation by setting the initial gimbal angle further from the singularity state. The presented control law was simulated in the MATLAB® SIMULINK® software. Results obtained from the simulation show the effectiveness of the control algorithm.
Publisher
Trans Tech Publications, Ltd.
Reference7 articles.
1. C. Clark, K. Worall, and E. Yavuzoğlu, A Control Moment Gyro for Dynamic Attitude Control of Small Satellites, 24th Annual AIAA, USU, Conference on Small Satellites, USA, (2010).
2. Bedrossian, N. S. et al, Steering Law Design for Redundant Single Gimbal Moment Gyroscope, Journal of Guidance, Control and Dynamics, 13(6), (1990).
3. S. Asghar, P. L. Palmer, and Roberts, Exact Steering Law for Pyramid-Type Four Control Moment Gyro Systems, AIAA/ASS Astrodynamics Specialist Conference and Exhibit, Colorado, (2006) pp.1-4.
4. Lappas V. J., A Control Moment Gyro (CMG) Based attitude Control System (ACS) for Agile Small Satellites, Doctoral Thesis, UK, (2002) pp.3-21.
5. Vadali S. R. et al, 1990, Preferred Gimbal Angles for Single Gimbal Control Moment Gyros, Journal of Guidance, Control and Dynamics, 13(6), (1990).
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1 articles.
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