Differential Game Based Guidance Law for High Angle of Attack Missiles.

摘要

A nonlinear differential game theoretic intercept guidance law for short range missiles is derived. Differential geometric transformations are used to convert the nonlinear missile and the target models into a convenient form for the formulation and solution of the guidance problem. Guidance law is then derived using the necessary conditions for optimality. Due to the inclusion of all the significant nonlinearities in the formulation, the guidance law is useful in advanced missiles executing large angle of attack maneuvers. The guidance law performance is illustrated in air-to-surface and air-to-air intercept missions.