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)


    Zugriff

    Zugriff über TIB

    Verfügbarkeit in meiner Bibliothek prüfen


    Exportieren, teilen und zitieren



    Titel :

    Optimal Controllers for Homing Missiles


    Beteiligte:
    G. Willems (Autor:in)

    Erscheinungsdatum :

    1968


    Format / Umfang :

    38 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch






    Neoclassical Guidance for Homing Missiles

    Pini Gurfil / Mario Jodorkovsky / Moshe Guelman | AIAA | 2001


    Hyperstable range in homing missiles

    TANAKA, TOSHIYUKI / EGUCHI, HIROFUMI | AIAA | 1990


    Optimal Guidance for Active Aircraft Defense Against Homing Missiles

    Garcia, Eloy / Casbeer, David / Pachter, Meir | AIAA | 2017