Homing guidance laws using applied fuzzy systems

Abstract

In this paper we present a simulation model of homing-guided anti-aircraft or surface-to air (SA) missiles-SAM, suitable for research, development and testing of different guidance and control laws, obtained from synthesis process. In homing-guidance systems for SA missiles-proportional navigation is most commonly used, and also improved solutions and optimal guidance laws based on modern control theory. In the synthesis of these laws-reduced and linearized models are used, which are obtained from general laws for mobile objects (target and missile) under some assumptions. All systems for guidance and control of SA missiles are complex and typically non-linear. Also there is a need for neutralizing of targets with high range of parameter changes (acceleration, velocity and height), in different shooting regimes (incoming, outgoing etc.). In order to provide quality process and small guidance error-we have applied fuzzy logic to obtain some parameters for the guidance law. In this paper we present results from investigation of different guidance laws for hypothetic SA missile. We have investigated classical proportional navigation-PN, augmented proportional navigation-APN, and optimal guidance laws for different shooting conditions. The results from fuzzy guidance law combined with proportional navigation are also given. Simulation programs are realized in FORTRAN and MATLAB.