Attitude control of spinning satellite subject to actuators restriction using eigenstructure assignment

• Published in: ISSCAA 2006 : 1st International Symposium on Systems and Control in Aerospace and Astronautics : January 19-21, 2006, Harbin, China / sponsored by China Space Agency ; co-sponsored by China Aerospace Science and Technology Corp [sic] ... [et al.] ; organiz pp. 7 pp. - 1419
• Main Authors: Bolandi, H., Bayat, F., Nasirian, M.
• Format: Conference Proceeding
• Language: English
• Published: IEEE 2006
• Subjects: Actuators; Algorithm design and analysis; Frequency domain analysis; Noise robustness; Optimal control; Robust control; Satellites; Sensor phenomena and characterization; Spinning; Torque control
• ISBN: 0780393953; 9780780393950
• DOI: 10.1109/ISSCAA.2006.1627503

In this paper, attitude control of spinning satellite equipped with double gimbals single rotor-control moment gyro (DGSR-CMG), based on linear quadratic Gaussian (LQG), and loop transfer recovery (LTR) is discussed. Actuator restriction to providing torque in satellite motivates us to design an optimal-robust multivariable controller by loop eigenstructure assignment, which overcomes this restriction. Design procedure consists of three stages: the first one is Kalman filter design as the best estimator. The second is an optimal control gain which would be obtained based on LQG method and the last step is loop transfer recovery at the output of plant based on LTR method. These procedures cause increasing robustness and performance of system. Algorithms and design strategies are investigated in frequency domain based on LQG/LTR method. Actuators saturation phenomenon has been considered and simulation results show that the designed controller is more robust against disturbances, sensor noise and actuators saturation