Slewing maneuver and vibration control of tethered space solar power satellite

Control approach is presented for vibration suppression of tethered space solar power satellite (SSPS) during slewing maneuver by combining attitude control and active vibration control based on tether tension. The mathematical description for the slewing motion of tethered SSPS is proposed. Mission Function (MF) Control Algorithm is applied in the design of a PD controller, which is able not only to stabilize the satellite attitude but also suppress vibration of the flexible solar panel. An additional active flexible control system, acting on the flexible parts can be desired for the further micro-vibration suppression, is designed by employing the MF control algorithm and the nonlinearity of the flexible tether is taken into account in the controller design. In the design process, the stability of the vibration control system is proved. Simulation results demonstrate the proposed approach can significantly reduce the vibration of the flexible solar panel during and after the maneuver operation.