TY  - JOUR
AU  - Kwon, Sangwon 
AU  - Tani, Yuki 
AU  - Okubo, Hiroshi 
AU  - Shimomura, Takashi 
PY  - 2010
TI  - Fixed-Star Tracking Attitude Control of Spacecraft Using Single-Gimbal Control Moment Gyros 
JF  - American Journal of Engineering and Applied Sciences
VL  - 3
IS  - 1
DO  - 10.3844/ajeassp.2010.49.55
UR  - https://thescipub.com/abstract/ajeassp.2010.49.55
AB  - Problem statement: A cluster of small-sized Single-Gimbal Control Moment Gyros (SGCMGs) is proposed as an attitude control actuator for high-speed maneuver of small satellites. There exists a singularity problem what is peculiar to the CMG system. Approach: This study presented a simple singularity avoidance steering law using the Singular Value Decomposition (SVD) algorithm. Results: Capability of the present steering method in singularity avoidance was demonstrated with numerical simulations for fixed-star tracking control of a small satellite using four SGCMGs. Conclusion: The proposed steering law utilizes the singular value decomposition to obtain singular vectors and generates the command gimbal rate that keeps the command torque in the direction orthogonal to the singular direction with a maximum gain.