Ducted tail rotor providing torque reaction and yaw attitude con

Details Ducted tail rotor providing torque reaction and yaw attitude con Ducted tail rotor providing torque reaction and yaw attitude con

1993-09-10

1995-05-16

Look, Edward K.

Fluid reaction surfaces (i.e., impellers)

Having positive means for impeller adjustment

Power or manual actuator on non-rotatable part

416164, 416245R, 416244R, B64C 2778

Patent

active

054155258

ABSTRACT:
A tail rotor for a rotary wing aircraft is located in a laterally directed duct located at the end of a tail cone extending rearward from the aircraft cabin and at the base of an empennage extending upward from the duct. The rotor includes a rotor shaft driveably connected to a power source, a rotor hub connected to the rotor shaft, a rotating control shaft, a stationary control shaft, and an actuator connected to the stationary control shaft for moving the rotating control shaft axially. The rotor hub includes rotor arms each supporting a pitch shaft for pivotable movement about a pitch axis. Each pitch shaft is adapted to support a rotor blade so that its angle of attack changes with movement of the pitch shafts. A pitch beam, located adjacent the rotor hub, supports flexure members, each connected to a pitch shaft eccentric of its pitch axis. The flexures driveably connect the pitch shafts to the pitch beam and transmit pitch control motion to the pitch shafts as the pitch beam moves along the rotor axis due to actuator input.

REFERENCES:
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patent: 3518025 (1970-06-01), Schmidt et al.
patent: 3610774 (1971-10-01), Mouille
patent: 3637321 (1972-01-01), Nekrasov et al.
patent: 3768334 (1973-10-01), Ditlinger
patent: 4281966 (1981-08-01), Duret et al.
patent: 4545733 (1985-10-01), Schwarz et al.
patent: 4585391 (1986-04-01), Vuillet et al.
patent: 4626173 (1986-12-01), Mouille et al.
patent: 5096381 (1992-03-01), Svenning
International Search Report/PCT/US92/06444/Jul. 31, 1992.

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