Optimal Missile Evasion

Abstract : The purpose of the study is to formulate a method to determine the control strategies that maximize the probability of survival for an evading aircraft against an air-to-air missile. The missile model developed is a typical infrared missile using proportional navigation steering. The P(k) is modeled as ellipsoidal iso-cost surfaces with a cost value that decays exponentially. The problem terminates when the line-of-sight from the missile to the target aligns on the edge of the missile's fuzing cone angle. The algorithm developed employs a second order differential dynamic programming model which optimizes the controls of the evading aircraft.