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

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 betw een the compensator output and the actuator control input, and is used to m ake the actuator work in linear ranges. When this type of controller was ap plied to the two-stage sounding rocket attitude control system, a remarkabl e improvement was made in the control performance as compared with the PID (proportional, integral, plus derivative) controller case. Since the perfor mance of this anti-wind-up controller was sensitive to the variation of con trol gains, a modified anti-wind-up controller has been also proposed to co mpensate for this.