Aircraft control system is designed to provide adequate stability during transition flight of a quad-tilt wing (QTW) UAV. The dynamic inversion method, which is a linearization method without an approximation algorithm, is applied to a control problem of the UAV, because of strong nonlinearity of its dynamical behavior. The validity of the proposed control system is verified through numerical simulation and experiment.


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    Title :

    Design of flight control system for quad tilt-wing UAV


    Contributors:


    Publication date :

    2015-06-01


    Size :

    675803 byte




    Type of media :

    Conference paper


    Type of material :

    Electronic Resource


    Language :

    English




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