Title: Robust attitude control of nano-satellite using control moment gyros based on higher order sliding modes
Authors: Ting Hao; Saburo Matunaga
Addresses: Department of Mechanical and Aerospace Engineering, Tokyo Institute of Technology, 2-12-1 Ookayama, Meguro-ku, Tokyo 152-8550, Japan ' Space Flight Engineering Department, Institute of Space and Astronautical Science (ISAS), Japan Aero Exploration Agency (JAXA), 3-1-1 Yoshinodai, Chuo-ku, Sagamihara, Kanagawa 252-5210, Japan
Abstract: Rapid attitude orientation and stable pointing accuracy are critical characteristics for observation missions of nano-satellite nowadays. This paper focuses on analysis of attitude control law for nano-satellite TSUBAME which is developed by Laboratory of Space System at Tokyo Institute of Technology. In recent years, the higher order sliding mode control (HOSMC) is considered, which is more useful in handling the chattering effect against external disturbance and unknown friction effects. Furthermore, HOSMC can remove the chattering effect if appropriate relative degree was chosen. To overcome the singularity problem inherent in the control moment gyros, a modified steering law for single gimbal control moment gyros (SGCMG), which aims at precisely exporting commanded torque is discussed based on the optimal output torque capability principle. This paper includes a comparison between two different control algorithms in the attitude controlling system which used control moment gyro (CMG) as the actuator for TSUBAME. The numerical simulation results demonstrate the efficiency and feasibility of the proposed HOSMC algorithm.
Keywords: higher order SMC; sliding mode control; control moment gyros; CMGs; chatter effect; robust control; attitude control; nanosatellites; satellite control; singularity; output torque capability; numerical simulation.
International Journal of Space Science and Engineering, 2014 Vol.2 No.3, pp.259 - 275
Received: 05 Mar 2014
Accepted: 03 May 2014
Published online: 04 Aug 2014 *