Aeronave diseñada como helicóptero híbrido con un fuselaje de aeronave (1), un rotor principal (2) dispuesto en el fuselaje de aeronave (1) y rotores cicloidales (3, 3') sobresalientes lateralmente del fuselaje de aeronave (1) con una superficie frontal exterior, caracterizada por que los rotores cicloidales (3, 3') están unidos al fuselaje de aeronave (1) mediante un dispositivo de suspensión (4, 4') que soporta cada uno de los rotores cicloidales (3, 3') por al menos uno de sus dos bordes exteriores y por que cada rotor cicloidal (3, 3') se puede controlar individual e independientemente del otro y los rotores cicloidales (3, 3') pueden ejecutar una compensación del par de giro del rotor principal (2).

    The invention relates to an aircraft designed as a compound helicopter with an aircraft fuselage, a main rotor arranged on the aircraft fuselage, and cyclogyro rotors which protrude laterally from the aircraft fuselage and which comprise an outer end surface. An improved torque compensation is achieved in that the cyclogyro rotors are connected to the aircraft fuselage by means of a suspension device which holds the cyclogyro rotors at the outer border of the rotors, and each cyclogyro rotor can be controlled individually and independently of the other. A torque compensation function of the main rotor can be carried out by the cyclogyro rotors.


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    Title :

    Aeronave


    Contributors:

    Publication date :

    2020-03-27


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    Spanish


    Classification :

    IPC:    B64C AEROPLANES , Flugzeuge



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