Continuous Terminal Sliding Mode Guidance Law with Consideration of Autopilot Dynamics

This paper proposes a new continuous terminal sliding mode guidance law for three-dimensional missile guidance system under maneuvering target with consideration of second-order autopilot dynamics. The proposed guidance law not only guarantees the azimuth rate and elevation rate of guidance system converge to zero in finite time but also ensures the continuity of control action. Simulations of a practical interception process under complex maneuvering target are carried and the simulation results demonstrate the effectiveness of the proposed guidance method.