The dynamic model of a high-performance military aircraft is considered. An input-output representation relating the open-loop pitch and heave rate characteristics to elevator movement is derived. Effective closed-loop design techniques are invoked. Simulated response transients are presented.


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    Titel :

    Aircraft pitch and heave rate control


    Beteiligte:
    Whalley, R (Autor:in) / Ebrahimi, M (Autor:in)


    Erscheinungsdatum :

    2000-01-01


    Format / Umfang :

    8 pages




    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Elektronische Ressource


    Sprache :

    Englisch




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