This paper presents a Hover Mode transition to Fast-Forward Mode flight control law of tilt-rotor UAV. A control law based on incremental nonlinear dynamic inversion is designed for tilt-rotor UAV, which has better robustness and lower model precision requirement compares to the nonlinear dynamic inversion control model. Firstly, the tilt-rotor UAV is introduced as experimental platform. In view of the redundancy of tilt-rotor aircraft, the control allocation algorithm of the control surface is designed, and the control of different kinds of control surfaces during the transition process is realized. Then, an incremental nonlinear dynamic inversion control law is derived based on the dynamic model of the tilt-rotor aircraft, which can be applied to different flight modes. Finally, simulation tests in hover mode to fast-forward mode show that the control law has good robustness and command tracking ability. In addition, sensitivity analysis of aerodynamic parameters provides us with some suggestions for adjusting the parameters in the actual flight test.


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    Titel :

    Design of Flight Control Law of Tilt-Rotor Aircraft Based on Incremental Nonlinear Dynamic Inversion


    Weitere Titelangaben:

    Lect. Notes Electrical Eng.


    Beteiligte:
    Yan, Liang (Herausgeber:in) / Duan, Haibin (Herausgeber:in) / Yu, Xiang (Herausgeber:in) / Tang, Peng (Autor:in) / Liu, Shuna (Autor:in) / Zheng, Chen (Autor:in)


    Erscheinungsdatum :

    2021-10-30


    Format / Umfang :

    14 pages





    Medientyp :

    Aufsatz/Kapitel (Buch)


    Format :

    Elektronische Ressource


    Sprache :

    Englisch





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