Volume 1 - Issue 4, November - December 2025

This paper presents a method for synthesizing optimal guidance laws for surface-to-air missiles during the remote control phase based on the standard trajectory method. In the initial stage of missile flight, remote control is crucial to ensure accurate transition to the homing phase and effective interception of maneuvering aerial targets. By establishing a standard reference trajectory and applying optimal control theory, the proposed approach minimizes trajectory deviations and control energy while maintaining high terminal accuracy. The standard trajectory method enables analytical determination of control commands that guarantee stable flight and rapid convergence toward the desired path. Simulation results demonstrate that the synthesized guidance law improves control precision, reduces response delay, and enhances overall missile–target engagement performance compared with conventional proportional navigation and linear feedback laws. The proposed method can be effectively applied to modern SAM systems to improve interception probability in complex air defense scenarios.