Deadbeat Nutation Controller for Momentum Bias Stabilized Spacecraft

A control procedure is presented for the deadbeat control of nutation in a one-axis momentum bias stabilization system. Nutation as well as attitude errors are brought to zero in finite time via a sequence of two control impulses. At the same time, the total control torque impulse is minimized subject to predefined constraints on the impulse size and bounds on the attitude errors. Being algorithmic, the controller is particularly suited for microcomputer implementation. In principle, any degree of control accuracy may be achieved through the definition of an appropriate "dead/one" in the control algorithm. The design flexibility of the proposed controller greatly surpasses that of the conventional pseudorate controller.