Abstract: The application of acceleration autopilot in spinning missile is restricted by the control coupling resulting from the actuator kinetics. A model of spinning missile autopilot is established, and the transfer function matrix of the equivalent actuator is derived. The methods of optimal actuator leading angle compensation and decoupling control based on dynamic output feedback are studied. Simulation results show that, with increase in the ratio of actuator band to rotating frequency, the control coupling becomes larger. The optimal actuator leading angle compensation is suitable for engineering application, but when the rotating frequency and the actuator frequency are increased, the decoupling effect deteriorates and the actuator control efficiency decreases. The complete decoupling can be achieved by using the method of decoupling control based on dynamic output feedback, and the measured errors have little effect on the application. However, this method needs a precise actuator kinetics model, and the complexity of compensator is closely related to the actuator order.

Key words: control science and technology, spinning missile autopilot, control coupling, decoupling algorithm, equivalent actuator, optimal actuator leading angle, dynamic output feedback