This invention relates to a missile system in which a missile is guided in a predetermined trajectory from launch or shortly thereafter in yaw by proportional navigation and in pitch. First the missile is guided by a pitch programmer until said missile reaches a predetermined angle between a line of sight of a seeker of the missile and a centerline of the missile, then in pitch by a time optimal controller to direct the missile at a predetermined angle toward a target and finally by proportional navigation in pitch of the missile to the target.


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    Title :

    Ideal Trajectory Shaping for Anti-Armor Missiles via Time Optimal Controller Autopilot


    Contributors:
    R. E. Yates (author) / J. P. Leonard (author) / R. E. Alongi (author)

    Publication date :

    1978


    Size :

    4 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English




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