This paper studies the design of a robust guidance law for missiles in the presence of uncertainties, which may include inaccurate prediction of target maneuver. Under the design, the closed-loop guidance system is shown to be robust to the uncertainties. 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 uncertainty) 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 demonstrate the benefits of the presented scheme.
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