A description of an attitude control system for a 3-axis stabilized spacecraft ispresented. Using modified Rodrigues parameters, a globally stabilizing nonlinearfeedback control law is derived that enables tracking of an arbitrary, time-varyingreference attitude. This new control incorporates integral feedback while avoidingany quadratic rate feedback components. A redundant cluster of four reactionwheels is used to control the spacecraft attitude, and three magnetic torquerods are used for purposes of continuous autonomous momentum dumping. Themomentum dumping strategy can employ general torque rod orientations, and isdeveloped to take advantage of a redundant set of reaction wheels.
展开▼
