A robust guidance law with predictable performance

This paper deals with the design of a robust guidance law for missiles in the presence of unknown target maneuver. Under the design, the closed-loop guidance system is shown to be robust to the target maneuver. Additionally, the scheme presented possesses the flexibility of allowing the engineer to select a desired guidance law for the nominal system (i.e., system without target maneuver) so that the state response of the overall uncertain guidance system is close to that of the selected nominal closed-loop guidance system. The simulation results clearly demonstrate the benefits of the presented scheme.