The question of attitude control and elastic mode stabilization of a spacecraft (orbiter) with beam-tip-mass-type payloads is considered. A three-axis moment control law is derived to control the attitude of the spacecraft. The derivation of the control moments acting on the spacecraft does not require any information on the system dynamics. The control law includes a reference model and a dynamic compensator in the feedback path. For damping out the elastic motion excited by the slewing maneuver, an elastic mode stabilizer is designed. The stabilization is achieved by modal velocity feedback using force and torque actuators located at the payload end of the elastic beam. Collocated actuators and sensors provide robust stabilization. Simulation results are presented to show that rotational maneuvers and vibration stabilization can be accomplished in the closed-loop systems despite the presence of model uncertainty and disturbance torque in the system.<>
Rotational maneuver of nonlinear uncertain elastic spacecraft
IEEE Transactions on Aerospace and Electronic Systems ; 24 , 2 ; 114-123
1988-03-01
811194 byte
Article (Journal)
Electronic Resource
English
Maneuver of distributed spacecraft
AIAA | 1984
|Nonlinear Input Shaping Control of Flexible Spacecraft Reorientation Maneuver
Online Contents | 1998
|Reorientation maneuver for spinning spacecraft
AIAA | 1991
|