Tail rotor yaw position control for a helicopter

Details Tail rotor yaw position control for a helicopter Tail rotor yaw position control for a helicopter

1986-09-30

1988-07-26

Barefoot, Galen

Aeronautics and astronautics

Aircraft, heavier-than-air

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

244 1719, 416 43, B64C 2782

Patent

active

047595140

ABSTRACT:
A yaw rate stabilizer for the tail rotor of a helicopter includes a tail rotor shaft rotatably supporting a tail rotor on which rotor blades are radially mounted to develop a lift force directed substantially horizontal and transverse to the longitudinal axis of the aircraft. A slider is provided connected by pitch links to the rotor. The angle of attack of the blades varies with the displacement of the slider relative to a rotor. The rotor shaft is mounted pivotably by a universal joint on the tail of the helicopter fuselage. A frame, pivotably aligned with the universal joint, is supported by a tension or compression spring and connected to a collective pitch transfer lever. The slider, which is slidably mounted on the rotor shaft, moves toward the tail rotor and increases the collective pitch of the blades as a result of the rotor pivoting at the universal joint to precession caused by a transient, yaw moment applied to the rotor by a transverse gust of wind. The blades develop increased lift directed opposite to the gust which opposes the yaw moment and stabilizes the aircraft.

REFERENCES:
patent: 2491191 (1949-12-01), Maillard et al.
patent: 3004736 (1961-10-01), Culver et al.
patent: 3211235 (1965-10-01), Brett
patent: 3404737 (1968-10-01), Keder, Jr.
patent: 3528633 (1970-09-01), Knemeyer
patent: 3532302 (1970-10-01), Dean

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