A New Missile Guidance Law Design based on Interception Point Strategy and Fuzzy Logic against High Maneuvering Targets

This paper presents a new hybrid guidance law based on classical interception point strategy and intelligent fuzzy logic methodology for missile guidance in the terminal phase for high maneuvering targets tracking. Due to the linear relationships of the missile -target engagement against the low maneuvering targets, the guidance law will be simply obtained based on the desired course angle of the missile. Since the missile-target engagement equations are highly nonlinear models, the guidance law solution against the high maneuvering targets is so complicated and time consuming. Therefore, the new guidance law against the high maneuvering targets is provided to calculate the interception point and time by using the obtained guidance law from the low maneuvering target and fuzzy logic. Performance comparisons are shown between the new fuzzy collision point (FCP) guidance law and the traditional sliding mode control, recently proposed augmented proportional navigation and collision point methods. Reducing in interception times besides the considerably improvement in control effort on four different missile-target engagement scenarios are among the achievements of the new hybrid method.