For the purpose of improving the accuracy of tilt-rotor aircraft model, a split modeling scheme is proposed instead of the overall modeling: the enhanced Pitt-Peters dynamic inflow model was used to describe the wake distortion effect, and the rotor-induced velocity distribution was modeled based on classical vortex theory and experimental data. Rotor download is taken into account in airfoil modeling, which is modeled by interference coefficient fitting method. The comparison experiments on publicly available data and modeling result prove the correctness of proposed model, and the proposed model can be used for the research of flight mechanics and control simulation of tilt-rotor aircraft with high accuracy.


    Access

    Check access

    Check availability in my library

    Order at Subito €


    Export, share and cite



    Title :

    Research on Mathematical Modeling Method of Tilt-Rotor Aircraft


    Additional title:

    Lect. Notes Electrical Eng.


    Contributors:
    Yan, Liang (editor) / Duan, Haibin (editor) / Deng, Yimin (editor) / Chen, Qiang (author) / Zhang, Ning (author) / Xue, Lulu (author) / Chen, Zefeng (author)

    Conference:

    International Conference on Guidance, Navigation and Control ; 2024 ; Changsha, China August 09, 2024 - August 11, 2024



    Publication date :

    2025-03-05


    Size :

    9 pages





    Type of media :

    Article/Chapter (Book)


    Type of material :

    Electronic Resource


    Language :

    English





    Mathematical modeling and control of a tilt-rotor aircraft

    Wang, Xinhua / Cai, Lilong | ArXiv | 2015

    Free access


    Four-rotor tilt rotor aircraft

    HONG QUAN / YE HONGCHUAN / CAI TIANXIAO | European Patent Office | 2020

    Free access

    The XV-15 tilt rotor research aircraft

    Dugan, D. C. / Erhart, R. G. / Schroers, L. G. | NTRS | 1980