采用框架角受限控制力矩陀螺的航天器姿态机动控制

doi:CNKI:11-1929/V.20110310.1710.002

Abstract

Abstract: This paper deals with the eigenaxis attitude maneuver of a spacecraft actuated by a control moment gyroscope (CMG) with gimbal angle constraints. Taking into consideration such as constraints actuator saturation and slew rate of spacecraft, some modifications are made to the previous attitude maneuver algorithm to ensure it can perform large angle eigenaxis maneuver. By introducing the proper magnitude of null motion to recombine the gimbal angles, a composite control steering logic is proposed for the CMG system with gimbal angle constraints, and a transform domain is also devised to eliminate chattering. Numerical simulations show that the proposed composite control steering logic can effectively utilize the control capacity of a CMG by recombining gimbal angles, and, combined with the attitude maneuver algorithm, realize eigenaxis rotation.

Key words: attitude control, eigenaxis maneuver, control moment gyroscope, steering law, gimbal angle constraint, composite control

CLC Number:

V488.22

GUO Yanning, LI Chuanjiang, ZHANG Yonghe, MA Guangfu. Spacecraft Attitude Maneuver Using Control Moment Gyroscope with Gimbal Angle Constraints[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2011, 32(7): 1231-1239.

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Spacecraft Attitude Maneuver Using Control Moment Gyroscope with Gimbal Angle Constraints

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