A description of an attitude control system for a three-axis stabilized spacecraft is presented. A globally stabilizing nonlinear feedback control law is derived that enables tracking of an arbitrary time-varying reference attitude. This new control incorporates integral feedback while avoiding any quadratic rate feedback components. A redundant cluster of four or more reaction wheels is used to control the spacecraft attitude, and three magnetic torque rods are used for purposes of continuous autonomous momentum dumping. The momentum dumping strategy can employ general torque rod orientations, and it is developed to take advantage of a redundant set of reaction wheels.
Three-Axis Attitude Control Using Redundant Reaction Wheels with Continuous Momentum Dumping
Journal of Guidance, Control, and Dynamics ; 38 , 10 ; 1865-1871
01.10.2015
Aufsatz (Zeitschrift)
Elektronische Ressource
Englisch
Three-Axis Attitude Control Using Redundant Reaction Wheels with Continuous Momentum Dumping
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