Developing integrated fuzzy guidance law for aerodynamic homing missiles by genetic algorithm
CEC'09 Proceedings of the Eleventh conference on Congress on Evolutionary Computation
Fuzzy Sets and Systems
Design of fuzzy logic missile guidance law with minimal rule base
FSKD'09 Proceedings of the 6th international conference on Fuzzy systems and knowledge discovery - Volume 6
CIRA'09 Proceedings of the 8th IEEE international conference on Computational intelligence in robotics and automation
Design of interceptor guidance law using fuzzy logic
FSKD'05 Proceedings of the Second international conference on Fuzzy Systems and Knowledge Discovery - Volume Part I
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How to develop a novel missile guidance law that can act effectively against very high speed incoming targets, such as ballistic missiles, has been a major concern in the defense technique. It has been unveiled recently in the literature that the most effective way for a lower speed interceptor to successfully engage an incoming target with very high speed is to limit the aspect angle between the missile and target flight path to within 180° plus or minus few degrees. On the basis of this requirement, a new integrated fuzzy guidance law is developed in this paper against very high-speed maneuverable targets on three-dimensional space. An integrated fuzzy type guidance law is explored for midcourse and terminal phases. It is shown that the integrated guidance scheme offers excellent tracking performance as well as performance sensitivity with respect to some parametric variations.