The invention relates to a hybrid multi-rotor aircraft with retractable wings, and mainly solves the problems in the prior art that the time of endurance is short and the load capacity is limited due to causes of structure. The hybrid multi-rotor aircraft with retractable wings mainly comprises motors, propellers, rocker arms, an aircraft body, a lithium battery pack, the retractable wings, retractable undercarriages and a flight control system; the assembly scheme of all the parts lies in that the propellers are mounted on the motors; the motors are fixed at one ends of the rocker arms through installation parts, and the other ends of the rocker arms are fixed in the middle of the aircraft body; the flight control system is mounted at the central position right above the aircraft body; the lithium battery pack is mounted at the central position under the aircraft body; the retractable undercarriages are symmetrically mounted at positions, close to the two sides, below the aircraft body; the retractable wings are fixed on the retractable undercarriages through installation parts. After the aircraft takes off, the undercarriages can be retracted, and at the same time the wings stretch towards outer sides, therefore the lift force of the multi-rotor aircraft is greatly increased, the time of endurance is prolonged, and the load capacity is further improved.


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    Titel :

    Hybrid multi-rotor aircraft with retractable wings


    Beteiligte:
    TONG GANG (Autor:in) / WANG FENG (Autor:in) / ZHOU GUOQING (Autor:in) / YANG KANG (Autor:in)

    Erscheinungsdatum :

    10.02.2016


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge



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