Evasion from a homing missile - Multiple model adaptive control approach

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, and nonlinear kinematics. Specific limiting cases are carefully analyzed in which the attacking missile uses proportional navigation, augmented proportional navigation, or optimal guidance. The optimal evasion strategies from a missile using such guidance laws are also presented. An extensive simulation study is used to demonstrate the viability of the proposed optimal evasion concept.