This paper considers the problem of rigid spacecraft. A nonlinear control law which uses the feedback of the unit quaternion and the measured angular velocities is proposed and is shown to provide global asymptotic stability. The control law does not require the knowledge of the system parameters, and is therefore robust to modeling errors. The significance of the control law is that it can be used for large-angle maneuvers with guaranteed stability.
Three-Axis Stabilization of Spacecraft Using Parameter-Independent Nonlinear Quaternion Feedback
1994
10 pages
Report
Keine Angabe
Englisch
Robust attitude stabilization of spacecraft using nonlinear quaternion feedback
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