An optimal slewing maneuver approach for a class of spacecraft with flexible appendages

Abstract On the attitude maneuvering problem of a class of spacecraft with flexible appendages, this paper proposes a control concept satisfying the both characteristics of the open-loop control of the rigid body modes in the sense of the maximum principle and the robust feedback control of the elastic vibration mode in the sense of the LQ regulator. Two candidates of control algorithms are proposed and discussed to satisfy this concept requirement. Their validity is verified through a ground-based hardware demonstration.