New Sliding Mode Control Approach for Rapid Attitude Maneuver Using Control Moment Gyros
Publication: Journal of Aerospace Engineering
Volume 29, Issue 2
Abstract
A single-gimbal control moment gyro (CMG) is considered to be an ideal torque-generating actuator for rapid attitude maneuvering due to its relatively large output torque. A new attitude control method that is based on the modified Rodrigues parameter (MRP) sliding mode control law for a pyramidal configuration using four CMGs is proposed. Robust inverse steering logic is used to avoid issues of the singularity of the CMGs. The proposed approach is expected to provide rapid and stable attitude maneuvering while avoiding the singularity of the CMGs. In addition, this method is demonstrated on a small satellite, named TSUBAME, designed by the Laboratory of Space Systems at the Tokyo Institute of Technology. The proposed control algorithm is verified through a Monte Carlo simulation and a software-in-the-loop attitude simulator for TSUBAME. The Monte Carlo simulation demonstrated that the new sliding mode control approach successfully tracks a time varying attitude for a nanosatellite model with a range of system uncertainties and unmodeled dynamics. The software-in-the-loop simulation results successfully demonstrated the efficacy and feasibility of the proposed control law.
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Acknowledgments
This research is granted by the Japan Society for the Promotion of Science (JSPS) through the “Funding Program for World-Leading Innovative R&D on Science and Technology (FIRST Program),” initiated by the Council for Science and Technology Policy (CSTP) and supported by JSPS KAKENHI Grant Number 26289329.
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Information
Published In
Journal of Aerospace Engineering
Volume 29 • Issue 2 • March 2016
Copyright
© 2015 American Society of Civil Engineers.
History
Received: Sep 20, 2014
Accepted: Jun 8, 2015
Published online: Aug 13, 2015
Discussion open until: Jan 13, 2016
Published in print: Mar 1, 2016
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