Position and control system for helicopter blade actuation

Details Position and control system for helicopter blade actuation Position and control system for helicopter blade actuation

1983-10-05

1985-08-13

Barefoot, Galen

Aeronautics and astronautics

Aircraft, heavier-than-air

Helicopter or auto-rotating wing sustained, i.e., gyroplanes

416160, 416170R, B64C 27605

Patent

active

045345244

ABSTRACT:
A helicopter blade position and control mechanism including a hollow rotor shaft for mounting a plurality of rotor blades with provision for pitch adjustment. A control shaft is disposed within the rotor shaft and is rotatable relative thereto and is associated with actuators for the blades such that the pitch of the blades is changed when the control shaft rotates relative to the rotor shaft. A planetary gear assembly interconnects the control shaft and a source of power fixed to the helicopter fuselage and is such that when an input to the planetary gear assembly is quiescent, the control shaft will rotate in the same direction and at the same rate as the rotor shaft to maintain a desired blade pitch. Conversely, when an input is placed on the planetary gear system, relative rotation between the control shaft and the rotor shaft will occur to provide the desired adjustment in blade pitch. The system allows accurate blade position feedback signals to be taken from a feedback device stationarily mounted on the fuselage.

REFERENCES:
patent: 1716134 (1929-06-01), Huguenin
patent: 1999091 (1935-04-01), Ebert
patent: 2224640 (1940-12-01), Bonawit
patent: 2417176 (1947-03-01), Ratie
patent: 2487836 (1949-11-01), Turnbull
patent: 3893789 (1975-07-01), Andrews

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