Evasion from a Homing Missile - Multiple Model Adaptive Control Approach

摘要

In this paper, a multiple model adaptive evasion strategy for a targetaircraft from a homing missile employing a linear guidance law isproposed. We assume arbitrary-order linear missile and target dynamics,bounded target control, and nonlinear kinematics. Specific limitingcases are carefully analyzed in which the attacking missile uses proportionalnavigation, augmented proportional navigation, or optimal guidance.The optimal evasion strategies from a missile using such guidancelaws are also presented. An extensive simulation study is used to demonstratethe viability of the proposed optimal evasion concept.