抄録
This research proposed a steering law of Control Moment Gyros(CMGs) to increase maneuverability and pointing accuracy for spacecraft attitude control. The steering law optimizes initial gimbal angles of CMGs in order to maintain higher manipulability and compensate inner torque disturbance due to the control error of gimbals. In addition, by doing calculation of optimizing initial gimbal angles before starting to maneuver actually, on-board computer resource will be used effectively. In order to verify the feasibility of the proposed steering law, 4CMGs, named skew type configuration, dynamics was modeled. The numerical simulations were carried out by giving rapid multitarget pointing mission of an agile earth-observing satellite. From the simulation results of gimbal motion among maneuvering, it is also shown that the proposed steering law can realize singularity avoidance and disturbance compensation.
