A main rotor system 12 of an aircraft 10 is provided including a first rotor 16 coupled to a transmission 25 and configured to rotate about an axis R in a first direction. A second rotor 18 is similarly coupled to the transmission 25 and is configured to rotate about the axis R in a second direction. At least the first rotor 16 includes an individual blade control system (IBCS) 50 configured to adjust a pitch of each of a plurality of blade 54 of the first rotor 16 independently. At least one slip ring 60 is configured to transmit electrical power and/or a control signal to the at least one IBCS 50.


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    Title :

    Swashplateless coaxial rotary wing aircraft


    Additional title:

    Taumelscheibenfreies Koaxialdrehflügelflugzeug
    Aéronef à voilure rotative coaxiale sans plateau cyclique


    Contributors:

    Publication date :

    2017-02-15


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    B64C AEROPLANES , Flugzeuge



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