A helicopter rotor blade control pitch link for transmitting movement of a rotating swashplate to a rotor blade pitch horn includes a spring module. The spring module includes at least one elastic member configured to generate link compliance when a force is transferred through the pitch link from the rotating swashplate to the rotor blade pitch horn. A plurality of such rotor blade control pitch links is used in a helicopter rotor blade control system having a swashplate assembly operatively connected to each of a rotor shaft and a rotor having a plurality of rotor blades with respective rotor pitch horns. Each rotor blade pitch link is configured to control a pitch of one rotor blade via the corresponding rotor blade pitch horn.
COMPLIANT HELICOPTER ROTOR PITCH LINK
2024-11-14
Patent
Electronic Resource
English
IPC: | B64C AEROPLANES , Flugzeuge |