Maneuver Attitude Control Method and In-Orbit Verification for Flexible Satellites with Single-Gimbal Control Moment Gyros.

The problems of the attitude maneuver control method and its actual application realization for flexible satellites are investigated. An attitude tracking controller which combines the PD control with compensation strategy is proposed, and the controller parameters, which can guarantee both system stability and wide-hand control, are achieved by employing the classical frequency-domain design technique for a flexible satellite system in case of time lag. In the control system implementation based on the control moment gyros (CMG), a novel CMG steering strategy by directly adjusting torque command vector is adopted to overcome the gimbal locked phenomenon of the traditional singularity robust steering law, as well as to avoid the singularity without exciting the flexible mode vibration. The effectiveness of the proposed method is sufficiently verified by an in-orbit flexible satellite. [ABSTRACT FROM AUTHOR]