The Angular Momentum Management Method Based on CMGs for the Fast Maneuvering Satellites

摘要

Due to the outstanding capability of control torque amplification and smoothly continuous output, Control Moment Gyro (CMG), as a new type of high-performance attitude control actuator of satellite, therefore has been adopted by more and more high-performance remote sensing satellites to implement the high temporal and spatial resolution of in-orbit application requirements. Based on the mission requirements of a certain spacecraft, this paper gives a detailed analysis of the utilization capacity of satellite actuators' angular momentum envelope under different CMG-group configurations. Within the design constraint of determined actuator configuration selection, the high-reliable ability of in-orbit singularity avoidance and high-efficient utilization ability on actuators' angular momentum are realized by designing and applying singularity avoidance method based on vector control, which lays a foundation for high-performance maneuvering of the satellite platform. In addition, in order to enhance the application effectiveness of satellite payloads, the proposed adjustment strategy of in-orbit bias angular momentum is applied. Moreover, the significant improvement on the maneuverability of the whole satellites specific direction is realized. Furthermore, the requirement that the single array camera can obtain the stereoscopic images of a single target with multiple shots in the same orbit is satisfied.