抄録
This study proposes a new Variable Speed Control Moment Gyros (VSCMG) steering law, which aims to achieve both agile attitude maneuvering and shortening of settling time for a control of a spacecraft. In the proposed steering law, an actuator acts like a typical Single Gimbal Control Moment Gyros (SGCMG) during agile maneuvering using an existing singularity avoidance steering law. And then an actuator acts like a VSCMG or Reaction Wheel (RW) during terminal attitude, which is required high accuracy attitude control in order to suppress torque error due to singularity avoidance and inner disturbance due to gimbal motion. This algorism results in shortening of settling time of a spacecraft. From the result of the numerical simulation, it is confirmed that the proposed steering law realizes high accuracy pointing control and shortening of settling time during a terminal attitude by compared with a typical and classical SGCMG singularity avoidance steering law.
