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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    Titel :

    Design of flight control system for quad tilt-wing UAV


    Beteiligte:


    Erscheinungsdatum :

    01.06.2015


    Format / Umfang :

    675803 byte




    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Elektronische Ressource


    Sprache :

    Englisch




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