Robust Nonlinear Attitude Control of Flexible Spacecraft

This paper presents an approach to large-angle rotationalmaneuvers of a spacecraft-beam-tip body configuration based onnonlinear invertibility and linear feedback stabilization. A controllaw Ud is derived for the decoupled control of attitude angles, lateralelastic deflections, slopes due to bending and angular deflection dueto torsion at the tip of the beam using torquers and force actuators.For the stabilization of the elastic modes, a linear feedback controllaw us is obtained based on a linearized model augmented with aservocompensator. Simulation results are presented to show thatlarge slewing and elastic mode stabilization can be accomplished.