INCREASING THE ACCURACY OF THE ANTI-AIRCRAFT MISSILE HOMING SYSTEM BY CHANGING THE PROPORTIONALTY COEFFICIENT OF THE HOMING LAW

This paper presents a method for improving the accuracy of an anti-aircraft missile homing system when engaging highly maneuvering targets by adjusting the proportionality coefficient of the guidance law. First, a mathematical model and the synthesis of the anti-aircraft missile homing system in the vertical plane are presented. Then, the dependence of the accuracy of the synthesized system on changes in the aerodynamic coefficients and the speed of the missile and the moment of the target's one-sided maneuver is investigated. A law for varying the proportionality coefficient and an algorithm for determining its parameters are proposed. To reduce the impact of interference on the system's accuracy, a Kalman filter is proposed. Simulation of the synthesized system is carried out using the Simulink environment. As a result, a high-accuracy anti-aircraft missile homing system is obtained.