Helicopter control system

Aeronautics and astronautics – Aircraft – heavier-than-air – Helicopter or auto-rotating wing sustained – i.e. – gyroplanes

Patent

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Details

244 6, 244 52, 244 23B, B64C 2782

Patent

active

047687371

ABSTRACT:
An anti-torque system for use in a helicopter has an aft mounted horizontal fan submerged within a fuselage mounted, upward facing plenum. The fan operates off the mainpower source. The plenum has two controllable exit ports for counter torque control, fuselage pitch control and yaw control. The controllable exit ports are located along the longitudinal direction of the fuselage and each are substantially opposite each other. One port has a sufficiently sized area to effectively offset the torque of the main rotor while the other port has a sufficiently sized area to effectively provide autorotative yaw control. Both ports can be used simultaneous or singly.

REFERENCES:
patent: 2420784 (1947-05-01), Larsen
patent: 2567392 (1951-09-01), Naught
patent: 2968453 (1961-01-01), Bright
patent: 3171614 (1965-03-01), Holmer
patent: 3179353 (1965-04-01), Peterson
patent: 3807662 (1974-04-01), Velazquez

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