Design of Missile with Two-Loop and Autopilot Yaw Using Root Locus

objective of this paper is to design an Automatic Landing Systemfor MISSILE based on Root Locus control system. The control method is used to define gains of the controllers to apply the Root Locus method. The block diagram of the proposed control system with required controller gains is presented. Based on automatic control principlesthe transfer functions for open and closed loop are obtained. The Root Locus for open loop is drawn and then gain (K) values are found for given damping ratios. Finally, the step responses of the closed-loop system with automatic landing system controller auto-pilot were drawn. The simulation results have proven the effectiveness of the proposed control system in terms of fast response in the presence of external disturbances.