Integral Sliding Mode Attitude Maneuver of Spacecraft With Consideration of Singularity Avoidance of Control Moment Gyros

Abstract To maintain and maneuver the attitude of large satellites representative of international space stations, and for small satellites requiring agile and large-angle attitude maneuvers, actuators are required that can provide high torque output. To solve this problem, a control moment gyro (CMG) is used, which is capable of generating a higher torque than a reaction wheel, which is conventionally used for attitude control. However, there are combinations of gimbal angles in CMG systems, called singularities, where torque cannot be output in a particular axis direction. The objective of this study is to construct an attitude control system for spacecraft that takes into account the singularity avoidance of CMGs. The effectiveness of proposed method is verified by the numerical simulation.