Helicopter tail rotor with pitch control mechanism

Details Helicopter tail rotor with pitch control mechanism Helicopter tail rotor with pitch control mechanism

1979-12-17

1982-07-20

Powell, Jr., Everette A.

Fluid reaction surfaces (i.e., impellers)

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

Resilient bias or mount

416141, B64C 2738, B64C 2778

Patent

active

043403352

ABSTRACT:
In a helicopter tail rotor of flexrotor or, composite bearingless rotor design, a control wheel member is positioned in spaced relationship to the torque tube at the blade inner end and is connected thereto by pivotal push-pull rods connected at one of their ends to the control wheel member and at their opposite ends to the leading edge and trailing edge of the torque tube so that, as the control wheel member is selectively caused to rotate relative to the blade, one push-pull rod pulls upon the torque tube while the other push-pull rod pushes upon the torque tube to cause the torque tube to rotate, and hence the flexible spar to which it is attached to twist to thereby selectively change the blade pitch angle.

REFERENCES:
patent: 2234503 (1941-03-01), Ray
patent: 2473299 (1949-06-01), Pitcairn
patent: 3211235 (1965-10-01), Bretl
patent: 3254725 (1966-06-01), Higgins
patent: 3506219 (1970-04-01), Mouille et al.

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