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).
ASSISTED COLLECTIVE PITCH CONTROL SYSTEM FOR A HELICOPTER ROTOR
UNTERSTÜTZTES SYSTEM ZUR KOLLEKTIVEN BLATTVERSTELLUNG EINES HUBSCHRAUBERROTORS
SYSTÈME DE CONTRÔLE ASSISTÉ DU PAS COLLECTIF D'UN ROTOR D'HÉLICOPTÈRE
22.11.2023
Patent
Elektronische Ressource
Englisch
IPC: | B64C AEROPLANES , Flugzeuge |
ASSISTED COLLECTIVE PITCH CONTROL SYSTEM FOR A HELICOPTER ROTOR
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