Helicopter yaw and propulsion mechanism

Details Helicopter yaw and propulsion mechanism Helicopter yaw and propulsion mechanism

1975-01-27

1976-05-18

Blix, Trygve M.

Aeronautics and astronautics

Aircraft, heavier-than-air

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

244 52, B64C 2782

Patent

active

039572269

ABSTRACT:
A mechanism is provided for controlling the directional heading of a helicopter, particularly during hover and autorotation. In addition the mechanism provides additional thrust which enables the helicopter to increase its maximum velocity. The mechanism includes three nozzles with valves positioned therein, located in the rearward portion of the helicopter fuselage. Two of the nozzles are located on opposite sides of the aircraft fuselage to provide thrust for use in controlling the directional heading of the aircraft. This thrust is also used to counteract the torque generated by the driving of the lifting rotor of the helicopter. The third nozzle is positioned so that the thrust generated by it will increase the forward velocity of the helicopter. A propeller or fan located in the body of the aircraft forces air from intakes through the fuselage to the nozzles. The position of the valves is determined by suitable control linkage.

REFERENCES:
patent: 3159360 (1964-12-01), Ryan et al.
patent: 3351304 (1967-11-01), Stein et al.
patent: 3545702 (1970-12-01), Laville et al.

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