In order to solve the problem of rotor airflow interference to the wing of tiltrotor UAV, the lift and drag in the slipstream area and the free flow area were calculated respectively according to the hydrodynamics theory and CFD simulation. The longitudinal nonlinear dynamics model of tiltrotor UAV is established by Newton-Euler method. In order to solve the problem that the lift and thrust are difficult to balance the body gravity in the transition flight mode, a method for calculating the transition corridor of a tiltrotor UAV without cyclic pitch is proposed. The boundary of the transition corridor is restricted by the Angle of attack of the wing and the thrust of the rotor. Considering the requirements of UAV cruise speed, flight safety and minimum energy consumption, the optimal transition curve is selected. The result show that the designed transition curve can ensure that the lift and the rotor thrust can balance the gravity completely and the Angle of attack is in a reasonable range, and the rotor force has enough margin of safety.


    Access

    Download


    Export, share and cite



    Title :

    Nonlinear modeling and transition corridor calculation of a tiltrotor without cyclic pitch


    Contributors:
    Fan Yourong (author) / Wang Xinhua (author) / Hu Zhe (author) / Zhang Kai (author)


    Publication date :

    2022




    Type of media :

    Article (Journal)


    Type of material :

    Electronic Resource


    Language :

    Unknown





    Influence of Pitch Attitude on Tiltrotor Autorotation Characteristics

    Vorwald, J. / AHS International | British Library Conference Proceedings | 2010


    Electronic control of blade pitch on a tiltrotor

    STAMPS FRANK BRADLEY / PARHAM JR THOMAS C | European Patent Office | 2024

    Free access

    ELECTRONIC CONTROL OF BLADE PITCH ON A TILTROTOR

    STAMPS FRANK BRADLEY / PARHAM JR THOMAS C | European Patent Office | 2021

    Free access