The present invention relates to the generation of an integrated guidance law for aerodynamic missiles. Particularly, a Tabu search-based approach is utilized for generating an integrated fuzzy guidance law, which includes three separate fuzzy controllers. Each of these fuzzy controllers is activated in a unique region of missile interception. The method includes the following steps: establishing a missile guidance law ƒ(z), where z represents a vector containing fuzzy membership functions and guidance rules associated with the missile guidance law; and 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 )  , where tƒ represents missile interception time, r represents a distance between the missile and a target, w1, w2 and w3 are weighting factors, and am represents a missile normal acceleration, and further |r(tƒ)|