[특허]Rotor/wing aircraft including vectorable nozzle

Rotor/wing aircraft including vectorable nozzle 원문보기

IPC분류정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	B64C-027/82 B64C-015/14 B64C-027/26 B64C-027/24 B64C-015/02 B64C-027/18 B64C-003/38
출원번호	US-0840979 (2017-12-13)
등록번호	US-10065735 (2018-09-04)
발명자 / 주소	Richardson, Steven D.
출원인 / 주소	The Boeing Company
대리인 / 주소	Hanley, Flight & Zimmerman, LLC
인용정보	피인용 횟수 : 0 인용 특허 : 37

초록

A method of operating an aircraft having a rotor/wing assembly and a nozzle comprises vectoring the nozzle into a position for creating vertical thrust, and using the rotor/wing assembly and the nozzle together to create vertical thrust during a rotary mode of operation.

대표청구항 ▼

1. A method of operating an aircraft having a rotor/wing assembly and a nozzle, the method comprising: vectoring the nozzle into a position for creating vertical thrust;using the rotor/wing assembly and the nozzle together to create vertical thrust during a rotary mode of operation, wherein the aircraft includes a turbine engine to produce an exhaust flow, wherein the rotor/wing assembly is configured to extract work from the exhaust flow and then direct the exhaust flow to the nozzle during the rotary mode of operation, wherein the rotor/wing assembly includes a rotor/wing and a turbine to drive the rotor/wing during the rotary mode of operation, the turbine including an inlet, a valve disposed in the inlet, an outlet, a vortical chamber and a chamber outlet, the inlet to receive the exhaust flow from the turbine engine, and wherein the aircraft includes a conduit fluidly coupling the outlet to the nozzle; andbypassing the rotor/wing assembly and using the nozzle to create forward thrust during a fixed mode of operation by operating the valve to direct the exhaust flow from the inlet to the outlet of the turbine. 2. The method of claim 1, wherein the position is a downward position, and wherein using the nozzle to create forward thrust during the fixed mode of operation includes vectoring the nozzle into an aftward position. 3. The method of claim 2, wherein the nozzle is disposed at an aft end of the aircraft. 4. The method of claim 1, wherein using the rotor/wing assembly to create vertical thrust during the rotary mode of operation includes operating the valve to direct the exhaust flow from the inlet, through the vortical chamber, to the chamber outlet. 5. The method of claim 4, wherein the conduit is a first conduit, and wherein the aircraft further includes a second conduit fluidly coupling the chamber outlet to the first conduit. 6. The method of claim 5, further including directing the exhaust flow from the second conduit to the first conduit during the rotary mode of operation, thereby providing the exhaust flow to the nozzle during the rotary mode of operation. 7. The method of claim 6, wherein the valve is a first valve, and wherein directing the exhaust flow from the second conduit to the first conduit includes operating a second valve disposed at a junction of the first conduit and the second conduit. 8. The method of claim 7, further including diverting a portion of the exhaust flow from the first conduit using the second valve to provide yaw control during the fixed mode of operation. 9. The method of claim 4, wherein the turbine is a radial inflow turbine. 10. The method of claim 5, further including diverting a portion of the exhaust flow from the second conduit to a yaw control system to provide yaw control during the rotary mode of operation. 11. The method of claim 10, wherein the yaw control system includes a left lateral outlet and a right lateral outlet. 12. The method of claim 11, wherein the valve is a first valve, further including operating a second valve to divert the exhaust flow to at least one of the left lateral outlet or right left lateral outlet. 13. The method of claim 11, wherein the left and right lateral outlets are near an aft end of the aircraft. 14. The method of claim 1, further including locking the rotor/wing to prevent rotation of the rotor/wing during the fixed mode of operation. 15. The method of claim 1, wherein the aircraft includes canards, and wherein the method further includes pivoting the canards during conversion between the fixed and rotary modes of operation. 16. The method of claim 1, wherein the aircraft includes a tail assembly, and wherein the method further includes pivoting the tail assembly during conversion between the fixed and rotary modes of operation. 17. The method of claim 1, further including independently controlling an amount of vertical thrust produced by each of the rotor/wing assembly and the nozzle.

이 특허에 인용된 특허 (37)

Nunnally,William C., Aircraft and hybrid with magnetic airfoil suspension and drive.
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Dornier ; Jr. ; deceased Claudius (Viehrutenweg 3 late of Hochstadt DEX) Dornier-Tiefenthaler ; legal representative by Martine (Viehrutenweg 3 D-8031 Hochstadt DEX) Windischbauer Florian (Buerlinsha, Aircraft with engine pods tiltable about a transverse axis.
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Girard Peter F. (La Mesa CA), Aircraft with retractable rotor wing.
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Wainfan Barnaby (Long Beach CA), Airplane with variable-incidence wing.
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Nyhus Daniel A., Articulating/telescoping duct for reaction drive helicopters.
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Rutherford John W. (Scottsdale AZ) O\Rourke Matthew (Newport News VA) McDonnell William R. (St. Louis MO) Smith Brian T. (Everett WA), Canard rotor/wing.
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Balmford David E. H. (Sherborne GB2), Compound helicopter with engine shaft power output control.
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Shenk, Barth W., Compound tilting wing for high lift stability and control of aircraft.
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Prewitt Richard H. (R.R. No. 3. 3585 Paris Pike Lexington KY 40511), Convertiblade.
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Bass, Steven M.; Mitchell, Clark A., Dual-flight mode tandem rotor wing.
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White, Bruce D., Fixed wing aircraft having powered rotor VTOL capability with rotor blades stowable during horizontal flight.
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Kress Robert W. (Saugerties NY), Four engine VTOL aircraft.
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Flanigan,Kenneth Warren, Gas-powered tip-jet-driven compound VTOL aircraft.
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Pham, Roger N, High performance VTOL convertiplanes.
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Pharris Jack W. (Alamogordo NM), High speed, long range turbo-jet aircraft.
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Heitmann Arnold M., Impeller for radial flow devices.
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Cunningham John T. (3559 High Mesa Dallas TX 75234), Lift-producing machine or device.
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Barocela,Edward; Vaporean,Charles N., Low-drag rotor/wing flap.
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MacInnes Hugh (La Canada CA), Method and apparatus for wastegating turbocharged engine with divided exhaust system.
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Pham Roger N. C., Rapidly-convertible roadable aircraft.
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Francois Daniel Claude,FRX ; Rieugnie Marc Jean-Luc,FRX, Rotary-wing aircraft of the compound type, and rear structural element for such an aircraft.
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Zimet, Nachman, Rotary-wing vehicle system.
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Osder Stephen S., Rotor blade swashplate-axis rotation and gyroscopic moments compensator.
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Franco Capanna IT, System to transform a horizontal take-off and self-sustained horizontal flight airplane into self-sustained horizontal flight, vertical landing and take-off, hybrid integrated airplane.
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Kress Robert W. (Saugerties NY), Tilt wing VTOL aircraft.
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Zimmermann Vincent H. (Olivette MO) DEGarcia ; Jr. Horacio J. (Maryland Heights MO) Pierson Harlan K. (Hazelwood MO), Trifan powered VSTOL aircraft.
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Clifton Robert T. (7999 Hansen ; #420 Houston TX 77061), V/STOL Aircraft.
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Koutsoupidis Theodore (12404 Harbor Dr. Woodbridge VA 22192), VTOL aircraft.
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Wooten ; Jr. William H. (Evendale OH) Speir Donald W. (Cincinnati OH), Vectorable nozzle.
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Szuminski Gary F. (Marietta GA) Nightingale Douglas J. (Jonesboro GA), Vectorable nozzles for aircraft.
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Kirla Stanley J., Vertical take off and landing aircraft.
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Robert P. Davis, Vertical take-off and landing vehicle configured as a compound autogyro.
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Einarsson, Einar, Vertical takeoff and landing aircraft.
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Lariviere Jean Soulez,FRX ITX 75008, Vertical takeoff and landing aircraft.
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Dickau, John Eugene, Vertical takeoff and landing aircraft propulsion systems.
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Cummings Darold B., Vertical/short take-off and landing (V/STOL) air vehicle capable of providing high speed horizontal flight.
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Binden John A. (Long Beach CA), X-wing helicopter-scout attack configuration.
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Rotor/wing aircraft including vectorable nozzle 원문보기

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