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. (Author)
Optimal Controllers for Homing Missiles
1968
38 pages
Report
No indication
English
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