Abstract
A cluster of small-sized single-gimbal control moment gyros (SGCMGs) is proposed as an attitude control actuator for high-speed maneuver of a small satellite. The singularity of the system of 4-SGCMGs in pyramid configuration is analyzed and the distribution of singularity surfaces is visualized. This paper also presents a new singularity avoidance control logic using the singular value decomposition algorithm. The effectiveness of the present singularity avoidance control logic is demonstrated with numerical simulations for a large angle maneuver of a small satellite.
