Optimal Controllers for Homing Missiles

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Abstract
Optimum control theory is applied to develop a guidance law for homing missiles. An existing, closed form, general solution of the 'minimum error regulator' problem is applied to a previously solved problem which uses a very simple plant model, in order to verify its applicability. The solution method is then applied to a system that includes autopilot lag, and in this case the optimum law is shown to differ from proportional navigation.

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