Guidance Law Design Using Intelligent Non-Linear Controller

Abstract

A sliding mode control algorithm combined with a fuzzy control scheme is developed for the trajectory control of a command guidance system. The acceleration command input is obtained. The proposed controller is used to compensate for the influence of unmodeled dynamics and to alleviate chattering. Simulation results show that the proposed controller gives good system performance in the face of system parameters variation and external disturbances. Moreover, the simulation results show the effectiveness of the proposed missile guidance law against different engagement scenarios.