Integration of a fuzzy guidance-control system for a command interceptor against hypersonic target

Extensive research efforts have been made to design or improve flight guidance and control systems. With the phenomenal growth in soft computing techniques, there is a growing interest to apply these techniques to missile flight guidance and control systems. This paper investigates the application of fuzzy logic for the development of fuzzy guidance laws for command-to-line-of-sight skid-to-turn (CLOS-STT) missile. The fuzzy logic guidance scheme based on the well known three-point guidance law is discussed. Preliminary studies have shown the advantages of using anti-air tactical missiles against hypersonic ballistic targets. A complete six-degrees-of-freedom (6-DOF)-flight model for an anti-air command guidance system is developed. Simulation results for this three-dimensional missile-target interception process are given to show the effectiveness of the proposed fuzzy guidance scheme.