Performance Analysis of A Missile Guidance and Control System Model for Precise Target Tracking

A missile navigation system model is developed and analyzed in this work. The flight command structure is a crucial component which improves the efficiency of the system. It has a major impact on both the accuracy of the strike and precise control over the missile's performance. The goal of the flight command structure is to instruct the missile to follow the steering directive produced by the control system. The system's representation is determined by how well it establishes the flying course required to intercept the target and sends the commands to the attitude control system required to keep the missile on course while taking the airframe's dynamics and relevant aerodynamic characteristics into account. The missile is guided to attack the target after it has been tracked, and its trajectory is determined by the homing guidance loop utilizing the PID controller-based autopilot mode. In the MATLAB simulation environment, dynamic performance of the missile guidance system is simulated using a step response technique based on time.