AN ADAPTIVE TAKAGI-SUGENO FUZZY GUIDANCE LAW WITH HIGH GAIN OBSERVER CONSIDERING MISSILE UNCERTAINTIES AND TARGET MANOEUVRE

This paper proposes an observer based adaptive Takagi-Sugeno fuzzy guidance law for a surface to air missile. An integrated guidance-control model is derived to consider target manoeuvre and missile uncertainties in the design process of the proposed guidance law, also use of adaptive intelligent system for approximation of unknown dynamic parts of the mentioned model and a high gain observer for estimation of required states caused that this approach, in contrast to guidance approaches introduced by now, use the minimum number of inputs for a robust missile guidance. Presented proofs and simulated results show the practical application and effective performance of designed guidance law.