The hybrid vertical takeoff and landing (VTOL) aircraft draw great attention from industrial and academic communities recently. In this paper, a nonlinear modeling process of a hybrid quad-tiltrotor aircraft under full-mode flight is proposed. Then, the developed nonlinear model is linearized at the equilibrium point and its stability characteristic is analyzed. Finally, simulation results show that the aircraft is trimmed at a transitional equilibrium point of rotor tilting angle of 45 \documentclass[12pt]{minimal} \usepackage{amsmath} \usepackage{wasysym} \usepackage{amsfonts} \usepackage{amssymb} \usepackage{amsbsy} \usepackage{mathrsfs} \usepackage{upgreek} \setlength{\oddsidemargin}{-69pt} \begin{document}$$45^ {\circ }$$\end{document} and velocity at 10.8 m/s, and it can keep straight level flight.


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    Title :

    Nonlinear Flight Dynamics Modeling of Hybrid Quad-Tiltrotor Aircraft Under Full-Mode Flight


    Additional title:

    Lect. Notes Electrical Eng.


    Contributors:
    Fu, Wenxing (editor) / Gu, Mancang (editor) / Niu, Yifeng (editor) / Lin, Qing (author) / Zhu, Xingyu (author) / Liu, Juhong (author) / Wang, Ban (author) / Huang, Jing (author)

    Conference:

    International Conference on Autonomous Unmanned Systems ; 2022 ; Xi'an, China September 23, 2022 - September 25, 2022



    Publication date :

    2023-03-10


    Size :

    10 pages





    Type of media :

    Article/Chapter (Book)


    Type of material :

    Electronic Resource


    Language :

    English




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