This paper presents an approach to large-angle rotational maneuvers of a spacecraft-beam-tip body configuration based on nonlinear invertibility and linear feedback stabilization. A control law u sub d is derived for the decoupled control of attitude angles, lateral elastic deflections, slopes due to bending and angular deflection due to torsion at the tip of the beam using torquers and force actuators. For the stabilization of the elastic modes, a linear feedback control law u sub s is obtained based on a linearized model augmented with a servocompensator. Simulation results are presented to show that large slewing and elastic mode stabilization can be accomplished.
Robust nonlinear attitude control of flexible spacecraft
1987-05-01
Miscellaneous
No indication
English
Robust nonlinear attitude control of flexible spacecraft
Tema Archive | 1987
|Robust Nonlinear Attitude Control of Flexible Spacecraft
IEEE | 1987
|Robust Nonlinear Attitude Control of Spacecraft with Flexible Structures
British Library Conference Proceedings | 2000
|Robust constrained fault-tolerant attitude control for flexible spacecraft
SAGE Publications | 2018
|