Helicopter engine torque compensator

Details Helicopter engine torque compensator Helicopter engine torque compensator

B - Operations, Transporting

64

C

244/17

B64C 27/78 (2006.01) G05D 1/08 (2006.01)

Patent

CA 1214149

Abstract Helicopter Engine Torque Compensator 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).

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