An assisted collective pitch control system for a helicopter rotor, wherein the helicopter (1) comprises a frame (2) defining a longitudinal axis (L) and a transverse axis (T), the system comprising a collective pitch control stick (10) rotatably mounted to the frame of the helicopter to rotate about a transverse axis (A), elastic means acting on the stick (10) to apply an auxiliary force (F, F') thereto, tending to reduce the pilot's effort. The system comprises assisted adjustment means which are designed to be controlled by the pilot and act on the elastic means to instantaneously changing the point of application (19) of the auxiliary force (F, F'). The shaft (12) is rigidly joined to a connecting arm (17) substantially perpendicular to the transverse axis (T) and axially offset from the stick (10). The elastic means comprise a spring (18) with one end articulated on a fixed point (19) of the helicopter frame and the opposite end fixed to a pin (20) associated with the connecting arm (17). The pin (20) is mounted to a slider (21 ) designed to slidingly move along said connecting arm (17).


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    Titel :

    ASSISTED COLLECTIVE PITCH CONTROL SYSTEM FOR A HELICOPTER ROTOR


    Weitere Titelangaben:

    UNTERSTÜTZTES SYSTEM ZUR KOLLEKTIVEN BLATTVERSTELLUNG EINES HUBSCHRAUBERROTORS
    SYSTÈME DE CONTRÔLE ASSISTÉ DU PAS COLLECTIF D'UN ROTOR D'HÉLICOPTÈRE


    Beteiligte:

    Erscheinungsdatum :

    22.11.2023


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge



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