Target evasion strategy against a finite set of missile guidance laws

In this paper, a multiple model adaptive evasion strategy for a target aircraft from a homing missile employing a linear guidance law is proposed. We assume arbitrary-order linear missile and target dynamics, bounded target control, nonlinear kinematics, and the missile employing one of a finite set of possible guidance laws. Specific cases are numerically analyzed in which the attacking missile uses proportional navigation, augmented proportional navigation, or optimal guidance. This effort was sponsored by U.S. Air Force Office of Scientific Research, Air Force Material Command, under grant number FA9550-15-1-0429. The U.S. Government is authorized to reproduce and distribute reprints for Governmental purpose notwithstanding any copyright notation thereon.