[특허]Systems and methods for rotor/wing aircraft

The Boeing Company

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특허 상세정보

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내보내기 페이스북 공유 트위터 공유 카카오톡 공유

Systems and methods for rotor/wing aircraft

특허상세정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	B64C-027/82
미국특허분류(USC)	244/017.19;
출원번호	US-0099724 (2008-04-08)
등록번호	US-8757537 (2014-06-24)
발명자 / 주소	Walliser, Eric W.
출원인 / 주소	The Boeing Company
인용정보	피인용 횟수 : 3 인용 특허 : 33

초록

Systems and methods for rotor/wing aircraft are disclosed. In one embodiment, an aircraft includes an airframe, a high-lift canard and tail, a rotor/wing, a propulsion system, and a drive assembly. The drive assembly, which may include a radial inflow turbine, is configured to extract work from the propulsion system to selectively rotate the rotor/wing assembly thus enabling the aircraft to conduct rotary-wing flight, fixed wing flight as well as smoothly transition between the two modes of flight.

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1. An aircraft comprising: a propulsion system;a rotor/wing assembly; anda radial inflow turbine assembly including a radial inflow turbine coupled to the rotor/wing assembly and configured to receive exhaust from the propulsion system during a rotational mode of operation and rotate the rotor/wing assembly, the turbine assembly configured to allow the exhaust to bypass the turbine and provide forward thrust during a second mode of operation. 2. The aircraft according to claim 1 wherein the propulsion system includes at least one engine that produces an exhaust flow, and wherein the radial inflow turbine assembly is configured to extract work from the exhaust flow. 3. The aircraft according to claim 1 wherein the propulsion system includes a vectorable nozzle assembly configured to controllably direct an exhaust flow between an approximately aftward direction and an approximately downward direction. 4. The aircraft according to claim 1, further comprising a yaw control system configured to provide a lateral force by exhausting a portion of an exhaust flow in a lateral direction. 5. The aircraft according to claim 1 further comprising a fuselage; wherein a rotational axis of the rotor/wing assembly extends generally upwardly with respect to the fuselage, and wherein the radial inflow turbine assembly is configured such that a drive portion of an exhaust flow is received into a body along an approximately radial direction with respect to the rotational axis, is deflected by a drive portion, and exits from the body approximately along the rotational axis. 6. The aircraft according to claim 5 wherein the drive assembly further includes a drive shaft projecting upwardly with respect to the fuselage and connected to the rotor/wing assembly; and wherein the radial inflow turbine assembly includes a turbine blade assembly coupled to the drive shaft and including a plurality of vanes that provide a rotational force when subject to the exhaust flow. 7. The aircraft according to claim 1 further comprising a fuselage and canards extending outward laterally from the fuselage; wherein each canard is pivotable between a first position configured to provide a lift force in a fixed-wing mode of operation, and a second position configured to minimize a downward force in a rotary-wing mode of operation. 8. The aircraft according to claim 1 further comprising a tail assembly pivotable between a first tail position configured to provide a lift force in the second mode of operation, and a second tail position configured to minimize a downward force in the first mode of operation. 9. A drive assembly for an aircraft having a propulsion system and a rotor/wing assembly, the drive assembly comprising: a radial inflow turbine assembly operatively coupled to the rotor/wing assembly and to the propulsion system and configured to extract work from the propulsion system to selectively rotate the rotor/wing assembly. 10. The drive assembly according to claim 9 wherein the propulsion system includes at least one engine that produces an exhaust flow, and wherein the radial inflow turbine assembly is configured to extract work from the exhaust flow. 11. The drive assembly according to claim 9 wherein the propulsion system includes at least one engine that produces an exhaust flow, and wherein the rotor/wing assembly rotates about a rotational axis, and wherein the radial inflow turbine assembly is configured such that a drive portion of the exhaust flow is received into a body along an approximately radial direction with respect to the rotational axis, is deflected by a drive portion, and exits from the body approximately along the rotational axis. 12. The drive assembly according to claim 11 wherein the radial inflow turbine assembly is configured to be coupled to the rotor/wing assembly by a drive shaft, and wherein the radial inflow turbine assembly includes a turbine blade assembly configured to be coupled to the drive shaft and including a plurality of vanes that provide a rotational force when subject to the exhaust flow. 13. The drive assembly according to claim 9, further comprising means for allowing the exhaust gas to bypass the turbine and provide forward thrust during a second mode of operation. 14. The aircraft according to claim 1, wherein the turbine assembly further includes a turbine body that forms a vortical chamber; wherein the radial inflow turbine is located in the vortical chamber; and wherein the turbine assembly further includes at least one inlet valve positioned within the body to selectively allow the exhaust to bypass the radial inflow turbine during the first mode and to direct the exhaust into the vortical chamber during the second mode. 15. The aircraft according to claim 1, wherein the turbine is coaxial with a hub of the rotor/wing assembly. 16. The aircraft according to claim 1, wherein the propulsion system includes first and second engines arranged side-by-side, and wherein the turbine assembly includes a housing for the turbine, the turbine housing having first and second inlets in fluid communication with the engines. 17. The aircraft according to claim 1, wherein the radial inflow turbine includes top vane portion and lower vane portion, the top vane portion having greater diameter than lower vane portion; and wherein the turbine assembly further includes a housing that forms a vortical chamber, the housing having an upper housing portion for housing the top vane portion and a lower housing portion for housing the lower vane portion. 18. The aircraft according to claim 17, wherein the housing is configured to direct exhaust gas from the propulsion system into the upper housing portion and then into the lower housing portion.

이 특허에 인용된 특허 (33)

이 특허를 인용한 특허 피인용횟수: 3

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Systems and methods for rotor/wing aircraft

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Systems and methods for rotor/wing aircraft

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이 특허에 인용된 특허 (33)

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