Authors
Abstract
This paper presents an optimal attitude maneuver by means of Reaction Wheels to achieve desired attitude for a Satellite. At first, Dynamic Equations of motion for a satellite with three Reaction Wheels as its active actuators has been educed, and then State Equations of this system has been obtained. In derivation of equations, coupling of Reaction Wheel electrical equations with dynamic equations of satellite motion, and Reaction wheel saturation avoidance approaches are considered. Then an optimal attitude control with the LQR method has exerted for a distinct satellite by its Reaction Wheels. As a result of simulation has presented an optimal effort by calculated Gain matrix to achieve desired attitude for chosen Satellite. It shows that satellite becomes stable in desired attitude with a low energy and time consumption.
Keywords
- Lai, L. Ch., Yang, Ch. Ch. and Wu, Ch. J., “Time-Optimal Maneuvering Control of a Rigid Spacecraft,” Acta Astronautica, Vol. 60, Issue 10-11, 2007, pp.791 – 800.
- Chen, X. and Steyn, W. H., “Optimal Combined Reaction-Wheel Momentum Management for LEO Earth-Pointing Satellites,” 12th AIAA/USU Conference on Small Satellites, 1998.
- Yoonhyeok, Ch., Hyunjae, L. and Hyochoong, B., “Optimal Reaction Wheel Steering Law for Saturation Avoidance,” Proceedings of the Aircraft Symposium, Vol. 43rd, pp. 65, 2005.
- Sidi, M. J., Spacecraft Dynamics and Control a Practical Engineering Approach, Cambridge University Press, 1997.
- کرک، دونالد. مقدمهای بر تئوری کنترل بهینه، ترجمة سیدکمالالدین نیکروش، دانشگاه صنعتی امیرکبیر، تهران، چاپ چهارم، 1382.
- Lyshevski, S. E., Electromechanical Systems, Electric Machines, and Applied Mechatronics, CRC Press, 2000.
- Pedersen, D. R., Grunnet, J. D., Larsen, J. A., Laursen, K. K., Kolakowska, E. and Amo, I. P., Attitude Control System for AAUSAT-II, Aalborg University, Institute of Electronic Systems, Project Period IAS8, February 2nd - June 2nd, 2004.
)