An approach to large-angle rotational maneuvers of a spacecraft-beam-tip body configuration is presented which is based on nonlinear invertibility and linear feedback stabilization. A control law 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 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
Robuste nichtlineare Lageregelung eines verformbaren Raumfahrzeugs
IEEE Transactions on Aerospace and Electronic Systems ; AES-23 , 3 ; 380-387
1987
8 Seiten, 17 Quellen
Article (Journal)
English
Robust nonlinear attitude control of flexible spacecraft
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