The patent describes a laser missile guidance system. A projectile or missile is fired toward a predetermined target. The missile is tracked on its flight toward the target by laser radar. The laser radar information is processed in a computer. A new trajectory is computed from the missile to the target. Correction signals are transmitted to a correction device on the missile, including thrusters on the missile, to cause the trajectory of the missile to be changed to the newly computed trajectory for the missile. This system corrects the trajectory of the missile while in flight by recomputing a trajectory from the missile to the predetermined target and making appropriate corrections each time. This enables the missile to only contain laser radar reflecting means, and correction detection and control means on the missile rather than having gyro and laser type devices on board the missile which take up a considerable amount of space and weight. (Author)


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    Titel :

    Laser Missile Guidance System


    Beteiligte:
    W. F. Otto (Autor:in) / W. B. McKnight (Autor:in) / J. J. Fagan (Autor:in)

    Erscheinungsdatum :

    1974


    Format / Umfang :

    5 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch




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