An anti-wind-up controller design for rocket control systems with control input saturation

Abstract

An anti-wind-up controller for the attitude control of a two-stage sounding rocket has been designed. Once the actuator comes up to saturation limits, a feedback signal is generated in this controller from the difference between the compensator output and the actuator control input, and is used to make the actuator work in linear ranges. When this type of controller was applied to the two-stage sounding rocket attitude control system, a remarkable improvement was made in the control performance as compared with the PID (proportional, integral, plus derivative) controller case. Since the performance of this anti-wind-up controller was sensitive to the variation of control gains, a modified anti-wind-up controller has been also proposed to compensate for this.