Output feedback detumbling and reorientation maneuvers of large flexible space structures by inversion

The question of rotational maneuver and vibration stabilization of the NASA Spacecraft Control Laboratory Experiment (SCOLE) System is considered. For the rotational maneuver, a control law (the orbiter control law) is derived using an orbiter input torque vector. Using this control law, detumbling and reorientation maneuvers of the SCOLE system are accomplished. Using the linearized model, a linear feedback control law is designed for vibration suppression. An observer is designed for estimating the state variables using sensor outputs which are also used for the synthesis of the control law. Extensive simulation results showed that rotational maneuvers of the spacecraft can be performed to follow precise angular velocity or attitude trajectories, and elastic modes can be stabilized using only output feedback