Steering law design to control moment gyroscopes for near minimum time attitude maneuver

摘要

In this paper a simple and more effective steering law is presented for spacecraft attitude maneuver with control moment gyroscopes (CMG) as actuator. The singularity problem and fast exchanging requirement of angular momentum are taken into consideration. Moreover, a near minimum time rest to rest eigenaxis rotation maneuver algorithm using CMG cluster is also proposed. Finally, simulations have been performed to demonstrate the effectiveness and advantages of the proposed steering law and maneuver algorithm.