Helicopter cyclic control assembly

Details Helicopter cyclic control assembly Helicopter cyclic control assembly

1995-12-01

1998-04-21

Morris, Lesley D.

Aeronautics and astronautics

Aircraft, heavier-than-air

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

244 1727, 244 1711, B64C 2752

Patent

active

057409870

ABSTRACT:
A helicopter cyclic control assembly for redirecting the thrust produced at a main rotor assembly includes a rotor disc control plate having arms with arm tubes therein for close, slideable insertion of slide rods, the slide rods being pivotally attached to bi-directional linear actuators, the bi-directional linear actuators being attached to the helicopter transmission casing or main truss works. The rotor disc control plate also having a neck tube with a bore which passes through the rotor disc control plate, through which an upper shaft passes and is rotatably engaged, the neck tube being perpendicular to the arm tubes. The upper shaft being fixedly attached at a distal end to the main rotor assembly, and rotatably engaged at a proximal end to a constant velocity joint such that as the motor is rotatably driving the upper shaft, the rotor disc control plate may be tilted relative to the helicopter body, the upper shaft tilting in cooperation with the rotor disc control plate, thereby changing the horizontal plane of the main rotor assembly, and redirecting the thrust produced at the main rotor assembly.

REFERENCES:
patent: 3118504 (1964-01-01), Cresap
patent: 3611367 (1971-10-01), Billottet
patent: 3921939 (1975-11-01), Garfinkle
patent: 4053123 (1977-10-01), Chadwick
patent: 4430045 (1984-02-01), Cresap

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