Rotor blade pitch control linkage

Details Rotor blade pitch control linkage Rotor blade pitch control linkage

1979-12-17

1981-10-27

Powell, Jr., Everette A.

Fluid reaction surfaces (i.e., impellers)

Articulated, resiliently mounted or self-shifting impeller...

Plural articulation

416114, 416138, 416168R, B64C 2738

Patent

active

042970806

ABSTRACT:
In a helicopter rotor, a blade control linkage is externally supported on the rotor hub and connected to the root end of a torque tube to provide torsion inputs to the blade by twisting the flexible spar member, which is enveloped by the torque tube and joined to the torque tube at a predetermined blade radial location. The linkage forms a parallelogram with the torque tube, and short vertical ball joint mounted links incline in two directions to accommodate blade lead/lag and flapping motions without introducing pitch coupling.

REFERENCES:
patent: 1676572 (1928-07-01), Oehmichen
patent: 1840148 (1932-01-01), Berry
patent: 3254725 (1966-06-01), Higgins
patent: 4222709 (1980-09-01), Mouille

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