Study on the effect of the modeling and filtering error sources on guidance laws of missile navigation

Abstract

The Proportional Navigation Guidance (PNG) law is not suitable for maneuvering targets interception as the accuracy will sharply degrade., in this paper, a modified augmented proportional navigation (MAPN) guidance law is proposed which adds an target maneuvering acceleration compensation to overcome the effect of the degradation of guidance accuracy. Aiming at modeling and filtering errors introduced by infrared seeker, engine and filter, such as the time delay of the seeker, the bias of the engine thrust, the time delay of the acceleration estimation, also the effect of the Extended Kalman Filtering (EKF) and Adaptive Extended Kalman Filtering (AEKF) on MAPNG law. Based on the presented analyses, the MAPN guidance law with the AEKF filter provides significant performance improvements over the commonly used classical method.