The optimal control theory is applied to the homing missile lateral autopilot design. The approach is to adapt the autopilot gains to the environment model reference and to vary as functions of time-to-go to minimize the performance index. The path constraint is applied throughput the whole terminal homing period and infinite penalty is imposed at intercept. A single-plane, linear autopilot design and implementation consideration are addressed for skid-to-turn (STT) case. Application to bank-to-turn (BTT) control is also discussed.


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    Title :

    Optimal controller for homing missile


    Additional title:

    Optimale Steuerung fuer gelenkte Flugkoerper


    Contributors:
    Yueh, W.R. (author) / Lin, C.F. (author)

    Published in:

    Publication date :

    1984


    Size :

    6 Seiten, 2 Tabellen, 6 Quellen


    Type of media :

    Conference paper


    Type of material :

    Print


    Language :

    English




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