Finite-Time Input-to-State Stability Guidance Law

Abstract

A new three-dimensional missile guidance law that guarantees the intercept of maneuvering targets in finite time is developed in this paper. The guidance law is designed via the finite-time input-to-state stability theory. It achieves a fast convergence rate and robustness to target maneuvers as well as an effective compensation for the missile autopilot dynamics. Distinct from the widely used sliding-mode-based guidance law design, prior knowledge of the upper bound of the target maneuver is not needed. The convergence time and convergence region can be controlled by adjusting the guidance parameters. The three-dimensional finite-time guidance law incorporating a first-order autopilot dynamics is designed by integrating the finite-time input-to-state stability theory with the backstepping method. Extensive simulation studies are provided to illustrate the advantages of the proposed guidance law over other guidance laws without the finite-time convergence property or without considering autopilot dynamics.