Robust nonlinear Attitude Control of Flexible Spacecraft

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 Ud 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 us is obtained based on a linearized model augmented with a servo compensator. Simulation results are presented to show that large slewing and elastic mode stabilization can be accomplished