Output feedback continuous terminal sliding mode guidance law for missile-target interception with autopilot dynamics

Abstract

This paper proposes an output feedback continuous terminal sliding mode guidance law (CTSMGL) for three-dimensional missile-target interception with consideration of second-order autopilot dynamics. The proposed output feedback CTSMGL not only guarantees the rates of the line-of-sight angles converge to zero in finite time but also ensures the continuity of control action. Besides, only the relative range and velocity information of guidance system has been utilized in its design process. Simulations of a practical interception process under three types of maneuvering targets are carried out and the simulation results illustrate the effectiveness of the proposed guidance method.