A leveraged pitch link designed to reduce the effects of vibration and shock from the rotary-wing aircraft main rotor blades and to reduce the energy required by utilizing leverage. Consequently, the leveraged pitch links improve the operating comfort and efficiency The objective of the invention is to provide a rotary-wing aircraft with improved flight characteristics that reduce vibration and reduce repairs and maintenance. The invention accomplishes these objectives by utilizing leverage to reduce the amount of energy required for cyclic and collective pitch control and by utilizing shock and vibration dampening connectors.


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    Title :

    ROTARY-WING AIRCRAFT LEVERAGED PITCH LINK


    Additional title:

    LIAISON DE PAS MOYENNE D'AERONEF A VOILURE TOURNANTE


    Contributors:

    Publication date :

    2016-06-22


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    B64C AEROPLANES , Flugzeuge



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