A linear quadratic based missile guidance law is presented that imposes a predetermined terminal body angle. Solutions are provided for arbitrary order autopilot dynamics, with explicit analytical expressions given for first-order and zero-lag dynamics. Performance is demonstrated through simulation in a planar interception scenario.


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    Title :

    Missile guidance with constrained intercept body angle


    Contributors:
    Rusnak, Ilan (author) / Weiss, Haim (author) / Eliav, Rei (author) / Shima, Tal (author)


    Publication date :

    2014-04-01


    Size :

    736431 byte




    Type of media :

    Article (Journal)


    Type of material :

    Electronic Resource


    Language :

    English



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