Abstract
In this paper, a new approach to design a control law for a missile guidance problem, based on desirable behavior of the state variables is proposed. The state variables in this problem may have three desirable behaviors, which are stability, asymptotically stability and even unstability. The proposed approach enables the missile to intercept a maneuverable target within a finite interception time which is less than existing approaches. Indeed, the main purpose of this paper is to decrease the interception time and it is shown that this new approach is realistic for missile guidance problems. Finally, the designed guidance law is simulated to show the effectiveness of the proposed method for interception of maneuvering and non-maneuvering targets.