Robust nonlinear Attitude Control of Flexible Spacecraft
IEEE Transactions on Aerospace and Electronic Systems
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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.
Actuators; Attitude control; Control systems; Force control; Open loop systems; Partial differential equations; Robust control; Space vehicles; Target tracking; Torque control
Aeronautical Vehicles | Aerospace Engineering | Electrical and Computer Engineering | Electrical and Electronics | Power and Energy | Propulsion and Power | Signal Processing | Space Vehicles | Structures and Materials | Systems and Communications | Systems Engineering and Multidisciplinary Design Optimization
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Singh, S. N.
Robust nonlinear Attitude Control of Flexible Spacecraft.
IEEE Transactions on Aerospace and Electronic Systems, 23