Abstract
Recently, it has been required agile control of satellites. For this purpose, the necessity of Control Moment Gyros (CMGs) has been increasing, which can generate much more torques. However, CMGs have a singularity problem. At singularities, the torque generated by the CMGs degenerates from three dimensions to two dimensions in the case of a specific set of angular momentum and angle of gimbals, and it may affect spacecraft attitude control performance. This study proposes a new steering control law for variable-speed control moment gyros (VSCMGs) designed for considering singular direction and maneuver direction using singular value decomposition. The proposed method is able to escape singularities more agile to change a specific set of angular momentum of gimbals.
