In a hybrid flight vehicle, having four rotors attached to a frame and configured to produce propelling force to propel the frame, a gas turbine engine attached to the frame and configured to rotate when fuel is supplied, a generator connected to an output shaft of the engine and configured to generate electric power when driven by the engine, a battery configured to store the electrical power generated by the generator, and four first electric motors each connected to the rotors to drive associated one of the rotors when the electric power is supplied from the battery, and an electronic control unit configured to control flight by regulating driving of the four rotors by the first electric motors. In the vehicle, the output shaft of the engine is attached parallel to at least one among yaw axis, pitch axis and roll axis of the frame.


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    Title :

    HYBRID FLIGHT VEHICLE


    Contributors:

    Publication date :

    2020-05-14


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

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



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