Helicopter engine torque compensator

Details Helicopter engine torque compensator Helicopter engine torque compensator

1982-04-16

1985-01-15

Barefoot, Galen L.

Aeronautics and astronautics

Aircraft, heavier-than-air

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

416 27, 416 43, 244 1721, B64C 2778

Patent

active

044934653

ABSTRACT:
The blade angle controlling pitch beam servo (26) of a helicopter tail rotor (22) is responsive to a signal manifestation (76) indicative of free turbine engine (20) gas generator speed (78) to provide torque compensation so that the helicopter airframe will not counter-rotate under the main rotor (10) of a helicopter as a consequence of the torque provided thereto by the airframe-mounted engine (20), or in the absence thereof. A trimming embodiment (FIG. 2) provides only sufficient blade angle command (82a) to compensate for that provided by fixed, collective/tail mixing (110-114). Torque compensation tail rotor blade angle commands may be applied through existing stability and autopilot actuators (30-32) or through an additional torque servo (120, FIG. 3).

REFERENCES:
patent: 2645293 (1953-07-01), Ogle et al.
patent: 2699833 (1955-01-01), Jensen
patent: 2985243 (1961-05-01), Tyler et al.
patent: 3174551 (1965-03-01), McCarthy
patent: 3200886 (1965-08-01), Magri et al.
patent: 3309868 (1967-03-01), Downing et al.
patent: 3603697 (1971-09-01), Lane
patent: 3833188 (1974-09-01), Robinson
patent: 4347997 (1982-09-01), Byham et al.

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