Missile Guidance Law Based on Extended State Observer

Abstract

The problem of missile interception is investigated in this paper. Sliding-mode controllers with finite-time convergence are proposed for the design of guidance laws. In particular, the control design consists of the estimation of the target acceleration by the extended state observer (ESO), and thus, it achieves the decrease of undesired chattering effectively. Also, simulation results are presented to illustrate the effectiveness of the control strategies.