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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    Title :

    Aircraft pitch and heave rate control


    Contributors:
    Whalley, R (author) / Ebrahimi, M (author)


    Publication date :

    2000-01-01


    Size :

    8 pages




    Type of media :

    Article (Journal)


    Type of material :

    Electronic Resource


    Language :

    English




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