Improving the performance of the missile guidance law in the presence of noise to intercept the maneuvering target

: Noise in a missile system can affect sensor readings and guidance accuracy, resulting in nav-igation mistakes. It may impair the autopilot, diminish aiming precision, and lower overall performance, particularly in electronic or signal-based systems that are susceptible to inter-ference or jamming. Another problem is target-maneuvering, it can pose a considerable chal-lenge to a tracking missile by changing the target's speed or direction, requiring the missile to constantly change its flight path. Rapid or erratic motions may create tracking problems, delay interception, or even result in a miss if the missile is unable to respond swiftly and pre-cisely. Guidance laws with constant coefficients cannot attain acceptable performance in all situations, particularly as noise and maneuvering increase. To maintain guidance accuracy despite target maneuvers and seeker noise, we introduce a variable guidance-law amplification factor whose discrete values are optimized with a genet-ic algorithm. The proportional-navigation coefficient is treated as a quantized variable and tuned so the controller adapts to changing target parameters, glint, receiver noise, Gaussian disturbances, and heading errors. Simulation across a wide range of engagement scenarios shows the optimized, variable coefficient consistently yields lower miss distances and the smallest percentage error even as target maneuvering intensity and noise amplification in-crease—performance that conventional fixed-coefficient methods struggle to match.