A Practical Approach for Rapid Maneuver of Small Agile Satellite using Micro-CMGs

摘要

Rapid attitude maneuver is one of key requirements of next generation satellites for advanced missions. Single-Gimbal Control Moment Gyro (CMG) can provide a greater agility than reaction wheel due to their torque amplification. However, the complex steering mechanism and the inherent singular problem limit the application of CMG. In this paper, a practical rapid attitude maneuver strategy using CMGs is proposed, considering synchronization operation of gimbal. A simple method for attitude trajectory guidance is developed based on the Euler's principal rotation theorem instead of using optimal control theory. Then nonlinear feedback control logic is used to obtain robustness against model errors and disturbances. The numerical simulations show that the proposed mixed control logic can achieve a large-angle and rapid maneuver with high robustness.