Finite-Time Guidance Law Design with Autopilot Dynamics Using Input-to-State Stability

摘要

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 (ISS) theory. It achieves 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, 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. Two simulation examples are provided to illustrate the advantages of the proposed guidance law over other similar guidance laws.