A battery powered helicopter uses one or more torque arms as the power source directly driving the main rotor blades, causing them to rotate. The helicopter does not require a combustion engine, a clutch, a reducer, a tail driver, a tail boom, a tail rotor, or a fuel supply system. The output shaft of the high-energy motor is coaxial with the main rotor shaft. The centrifugal force of one or more motor(s) is negligible or minimized. The torque arm assembly includes a plurality of torque arms. Each of the torque arms of the plurality of torque arms includes a propeller and a driving system. The torque arm propellers are hinged so that they can move between a first closed position and a second open position to institute an autorotation safety system.


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    Title :

    ELECTRIC TORQUE ARM HELICOPTER WITH AUTOROTATION SAFETY LANDING SYSTEM


    Contributors:
    DONG DAWEI (author)

    Publication date :

    2021-09-30


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    B64C AEROPLANES , Flugzeuge / B60L PROPULSION OF ELECTRICALLY-PROPELLED VEHICLES , Antrieb von elektrisch angetriebenen Fahrzeugen / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT



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    DONG DAWEI | European Patent Office | 2021

    Free access

    Optimal landing of a helicopter in autorotation

    Lee, Allan Y. / Bryson, Arthur E., Jr. / Hindson, William S. | NTRS | 1988


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    Optimal landing of a helicopter in autorotation

    Lee, A. Y. / Bryson, A. E., Jr. / Hindson, W. S. | NTRS | 1986