Patent ID: 8346690

Claim:
A computerized method of generating an integrated fuzzy-based guidance law, comprising the steps of: a) establishing a missile guidance law ƒ(z), wherein z represents a vector containing fuzzy membership functions and guidance rules associated with the missile guidance law; b) recording the missile launch guidance law ƒ(z) and the vector z in non-transitory computer readable memory; c) optimizing the missile launch guidance law ƒ(z) by minimizing the equation f ⁡ ( z ) = w 1 ⁢ t f + w 2 ⁢ ∫ 0 t f ⁢ a m 2 ⁢ ⅆ t + w 3 ⁢  r ⁡ ( t f )  , wherein t ƒ represents missile interception time, r represents a distance between the missile and a target, w 1 , w 2 and w 3 are weighting factors, and a m represents a missile normal acceleration, and further |r(t ƒ )|<r miss-allowed , where r miss-allowed represents a pre-selected allowable miss distance, wherein the minimization is performed by Tabu search; d) recording the optimized missile launch guidance law ƒ(z) in the non-transitory computer readable memory; and e) displaying the missile launch guidance law ƒ(z) to a user.