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)


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    Title :

    Optimal Controllers for Homing Missiles


    Contributors:
    G. Willems (author)

    Publication date :

    1968


    Size :

    38 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English






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