To further enhance the take-off, landing, hovering, and shuttling capabilities of micro-rotor drones in complex environments and implement lightweight design for the entire aircraft, a fuselage tilting tri-rotor UAV structure is proposed, which adopts the form of twin steering engines on the tail to realize fixed-angle tilt flight and hovering. In this paper, the unsteady aerodynamic interference phenomena between rotor-rotor and rotor-fuselage at different fuselage tilt angles (0° ~ 20°) are numerically investigated by using the sliding mesh model. The results demonstrate that this configuration allows the fuselage to be tilted and hovered from 0° to 20°. The fuselage tilts from 0° to 15° and 20°, resulting in respective increases of individual rotor input power by 16.7% and 46.6%. Furthermore, the hover efficiency decreases from 0.6262 to 0.5422 as the fuselage tilts from 0° to 20°. The fuselage should not be tilted at an angle greater than 15°, combining the effects of aerodynamic disturbances. Relevant conclusions can provide a reference for the design and flight control of the tri-rotor UAV with tilted fuselage.


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    Titel :

    Research on Aerodynamic Interference of a Tri-Rotor UAV With Tilted Fuselage


    Weitere Titelangaben:

    Springer Aerospace Techn.


    Beteiligte:
    Zhu, Zheng Hong (George) (Herausgeber:in) / Wei, Xiaohui (Herausgeber:in) / Li, Renfu (Herausgeber:in) / Qing, Liming (Autor:in) / Yuan, Ying (Autor:in) / Zhang, Qing (Autor:in) / Yang, Chengchuan (Autor:in) / Zhou, Haoyu (Autor:in)

    Kongress:

    International Conference on Advanced Unmanned Aerial Systems ; 2024 ; Nanchang, China September 20, 2024 - September 22, 2024



    Erscheinungsdatum :

    18.03.2025


    Format / Umfang :

    10 pages





    Medientyp :

    Aufsatz/Kapitel (Buch)


    Format :

    Elektronische Ressource


    Sprache :

    Englisch




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