The question of attitude control and elastic mode stabilization of a spacecraft (orbiter) with 'beam-tip mass' type payload is considered. It is assumed that bounded but unknown disturbance torques are acting on the spacecraft. Based on variable structure system (VSS) theory, a discontinuous three-axis moment control law is derived to control the attitude of the spacecraft. Although, this control law accomplished attitude trajectory tracking, it excites the elastic modes of the beam. A modal velocity feedback design is presented to damp the elastic oscillations using additional actuators at the top of the beam. Simulation results are presented to show that rotational maneuvers and vibration stabilization can be accomplished in the closed-loop system in spite of disturbance torques and uncertainty in the system. Reprints. (rrh)
Variable Structure Attitude Control and Elastic Mode Stabilization of Flexible Spacecraft
1989
7 pages
Report
No indication
English
Astronautics , Actuators , Attitude control systems , Attitude(Inclination) , Closed loop systems , Control , Control theory , Elastic properties , Feedback , Flexible structures , Maneuvers , Oscillation , Reprints , Rotation , Simulation , Spacecraft , Stabilization , Torque , Tracking , Trajectories , Variables , Velocity , Vibration , Flexible spacecraft , Satellite attitude control , Attitude control
Attitude Stabilization of Large Flexible Spacecraft
AIAA | 1981
|Attitude stabilization of large flexible spacecraft
AIAA | 1978
|