A hybrid-power system for a multi-rotor-wing aircraft, including: an engine (2); a power battery (5); a starter-generator integrated electric machine (7), the starter-generator integrated electric machine (7) is electrically connected to the power battery (5), and is mechanically connected to the engine (2), and power that is outputted by at least one of the engine (2) and the starter-generator integrated electric machine (7) is supplied to a main rotor wing (300) of the multi-rotor-wing aircraft; an auxiliary-rotor-wing electric motor (10), wherein the auxiliary rotor-wing electric motor (10) is electrically connected to the power battery (5), and an output of the auxiliary-rotor-wing electric motor (10) is mechanically connected to an auxiliary rotor wing (200) of the multi-rotor-wing aircraft, wherein the auxiliary rotor wing (200) comprises four auxiliary rotor wings, and a diameter of blades of the auxiliary rotor wings is 850mm 900mm; and a hydrogen balloon (11), located over a center-of-gravity central axis of the multi rotor-wing aircraft and mechanically connected to the multi-rotor-wing aircraft. The multi rotor-wing aircraft that uses the hybrid-power system according to the present disclosure can be flexibly controlled, has a good safety performance, has a high carrying capacity, saves oil and has a long endurance. - C>1


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    Title :

    HYBRID-POWER SYSTEM FOR MULTI-ROTOR-WING AIRCRAFT AND MULTI-ROTOR-WING AIRCRAFT


    Contributors:
    ZHANG HAITAO (author) / GUAN NANXIANG (author) / ZHOU MING (author)

    Publication date :

    2021-03-11


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / B64C AEROPLANES , Flugzeuge



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