US 12,252,242 B2
Compliant helicopter rotor pitch link
Conor Briggi, Philadelphia, PA (US); and Todd Waaramaa, Chandler, AZ (US)
Assigned to The Boeing Company, Arlington, VA (US)
Filed by The Boeing Company, Arlington, VA (US)
Filed on May 9, 2023, as Appl. No. 18/314,601.
Prior Publication US 2024/0375771 A1, Nov. 14, 2024
Int. Cl. B64C 27/72 (2006.01); B64C 27/605 (2006.01)
CPC B64C 27/72 (2013.01) [B64C 27/605 (2013.01); B64C 2027/7255 (2013.01)] 19 Claims
OG exemplary drawing
 
1. A helicopter rotor blade control system comprising:
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, the swashplate assembly including:
a stationary swashplate mounted on the rotor shaft; and
a rotating swashplate rotatably mounted to the stationary swashplate via a swashplate bearing; and
a plurality of pitch links configured to transmit movement of the rotating swashplate to the rotor pitch horns for controlling a pitch of each rotor blade;
wherein each pitch link includes a spring module having a plurality of Belleville springs configured to generate link compliance when a force is transferred through the respective pitch link from the rotating swashplate to a corresponding rotor blade pitch horn; and
wherein at least some of the plurality of Belleville springs are arranged in parallel.