[특허]Helicopter yaw and propulsion mechanism

Helicopter yaw and propulsion mechanism 원문보기

IPC분류정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	B64C-027/82
출원번호	US-0544077 (1975-01-27)
발명자 / 주소	Daggett Jr. Myron L. (Broomall PA) Douglas Leon L. (Wynnewood PA)
출원인 / 주소	The Boeing Company (Seattle WA 02)
인용정보	피인용 횟수 : 26 인용 특허 : 0

초록 ▼

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.

대표청구항 ▼

A helicopter which includes: a fuselage; a vertical stabilizer connected to said fuselage; a rudder connected to said stabilizer; a single main lifting rotor rotatably connected to said fuselage for lifting and propelling said helicopter; a motor connected to said fuselage and rotatably connected to said rotor; and a mechanism for controlling yaw and providing thrust augmentation to aid in propelling the helicopter forward which comprises: an air inlet in said fuselage; a duct positioned in said fuselage, connected at one end thereof to said inlet so that air may pass through said inlet to said duct; a first nozzle positioned in the rear portion of said fuselage, connected to said duct so air may pass from said duct and exit through said first nozzle generating a force which acts in a first direction tending to counteract torque generated when said motor drives said rotor; a second nozzle positioned in the rear portion of said fuselage on the side thereof opposite said first nozzle connected to said duct so air may pass from said duct and exit through said second nozzle thereby generating a force which acts in a second direction opposite said first direction; a third nozzle positioned in the rear portion of said fuselage connected to said duct so air may pass from said duct and exit through said thrid nozzle generating a force which acts in a third direction tending to propel said aircraft forward; a first valve mounted in said first nozzle for controlling the volume of air which may pass there through; a second valve mounted in said second nozzle for controlling the volume of air which may pass there through; a third valve pivotally mounted in said third nozzle for controlling the volume of air which may pass there through; a fan mounted in said duct for driving air from said inlet to said nozzles, operably connected to said motor; and a control means, including a pilot operable member connected to said rudder, connected to said fuselage, and connected to said first, second and third valves to vary the position of said valves, said control means maintaining said second and third valves in a closed position below a predetermined first velocity of the helicopter while varying the position of said first valve in response to pilot movements of said pilot operable member, said control means maintaining said first and second valves in a closed position above a predetermined second velocity of the helicopter while maintaining said third valve in an open position, and said control means varying the position of said second valve in response to pilot movements of said pilot operable member below said first predetermined velocity in the event autorotation occurs so that the forces generated by said first nozzle and said second nozzles cooperate to control the yaw of said aircraft.

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Groen, David L., Use of auxiliary rudders for yaw control at low speed.
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Binden John A. (Long Beach CA), X-wing helicopter-scout attack configuration.
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A62B-1/08	.. 윈치 또는 풀리에 제동기구가 있는 것

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