[특허]Tilt-rotor vertical-lift aircraft

The Boeing Company

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특허 상세정보

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Tilt-rotor vertical-lift aircraft

특허상세정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	B64C-015/12 B64D-035/00 B64C-029/00 B64D-035/08
출원번호	US-0315109 (2014-06-25)
등록번호	US-9475585 (2016-10-25)
발명자 / 주소	Hong, Alicia Newman, Daniel I. Holtorf, Christopher R. Chisholm, John R. Dyess, Stephen
출원인 / 주소	The Boeing Company
대리인 / 주소	Kunzler Law Group, PC
인용정보	피인용 횟수 : 1 인용 특허 : 8

초록

Described herein is an aircraft that includes a fuselage with a higher portion and a lower portion. The aircraft also includes two fixed wings that are coupled to and extend from opposing sides of the lower portion of the fuselage. Additionally, the aircraft includes a tilt-rotor assembly that is coupled to each of the two fixed wings.

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1. An aircraft, comprising: a fuselage comprising a higher portion and a lower portion;two fixed wings coupled to and extending from opposing sides of the lower portion of the fuselage;a tilt-rotor assembly coupled to each of the two fixed wings;at least two engines, non-movably coupled to each of the two fixed wings at locations on the two fixed wings between the fuselage and a respective one of the tilt-rotor assemblies;a common power transmission system, operatively coupling the tilt-rotor assemblies to the at least two engines coupled to each of the two fixed wings, wherein the common power transmission system comprises:a mid-wing gearbox positioned within the fuselage between the two fixed wings;a first driveshaft that extends between the mid-wing gearbox and a first of the tilt-rotor assemblies and a second driveshaft that extends between the mid-wing gearbox and a second of the tilt-rotor assemblies, wherein the mid-wing gearbox evenly distributes mechanical rotational energy between the first and second driveshafts at least while all of the at least two engines, non-movably coupled to each of the two fixed wings, are operable; andat least four driveshaft gearboxes coupled to the two fixed wings, wherein each of the at least four driveshaft gearboxes is in power receiving communication with a respective one of the at least two engines, coupled to each of the two fixed wings, and each of the at least four driveshaft gearboxes evenly distributes mechanical rotational energy from the respective one of the at least two engines, coupled to each of the two fixed wings, to respective sections of one of the first and second driveshafts coupled with each of the at least four driveshaft gearboxes;wherein: each tilt-rotor assembly comprises blades, rotatable about a common plane of rotation, and rotation of the first and second driveshafts rotates the blades of the first and second of the tilt-rotor assemblies, respectively;each tilt-rotor assembly is rotatable, relative to the two fixed wings, between a vertical orientation, in which the common plane of rotation is a horizontal plane, and a horizontal orientation, in which the common plane of rotation is a vertical plane, perpendicular to the horizontal plane; andthe blades of each tilt-rotor assembly rotate about the horizontal plane, to generate the entire lift and no forward thrust of the aircraft, and about the vertical plane, to generate the entire forward thrust and no lift of the aircraft. 2. The aircraft of claim 1, wherein each of the tilt-rotor assemblies is coupled to a tip of a respective fixed wing. 3. The aircraft of claim 1, wherein each of the first driveshaft and the second driveshaft extends along a respective one of the two fixed wings. 4. An aircraft, comprising: a fuselage;first and second fixed wings coupled to and extending from opposing sides of the fuselage;first and second tilt-rotor assemblies coupled to the first and second fixed wings, respectively;at least two first engines non-movably coupled to the first fixed wing; andat least two second engines non-movably coupled to the second fixed wing;wherein the at least two first engines and the at least two second engines are operatively coupled to both the first and second tilt-rotor assemblies via a common power transmission system that comprises: a mid-wing gearbox positioned within the fuselage between the first and second fixed wings;a first driveshaft that extends between the mid-wing gearbox and the first tilt-rotor assembly and a second driveshaft that extends between the mid-wing gearbox and the second tilt-rotor assembly, wherein the mid-wing gearbox evenly distributes mechanical rotational energy between the first and second driveshafts at least while all of the at least two first engines and at least two second engines are operable; andat least four driveshaft gearboxes coupled to the first and second fixed wings, wherein each of the at least four driveshaft gearboxes is in power receiving communication with a respective one of the at least two first engines and at least two second engines, and each of the at least four driveshaft gearboxes evenly distributes mechanical rotational energy from the respective one of the at least two first engines and at least two second engines to respective sections of one of the first and second driveshafts coupled with each of the at least four driveshaft gearboxes. 5. The aircraft of claim 4, wherein each of the first driveshaft and second driveshaft extends along a respective one of the first and second fixed wings. 6. The aircraft of claim 4, wherein the common power transmission system comprises at least two first engine gearboxes in power receiving communication with a respective one of the two first engines, and at least two second engine gearboxes in power receiving communication with a respective one of the two second engines, and wherein the two first engine gearboxes and the two second engine gearboxes are in power providing communication with a respective one of the at least four driveshaft gearboxes of the common power transmission system. 7. The aircraft of claim 4, wherein the at least two first engines are arranged in a side-by-side configuration, and the at least two second engines are arranged in a side-by-side configuration. 8. The aircraft of claim 4, wherein the at least two first engines are arranged in an end-to-end configuration, and the at least two second engines are arranged in an end-to-end configuration. 9. The aircraft of claim 4, wherein the at least two first engines are arranged in a staggered configuration, and the at least two second engines are arranged in a staggered configuration. 10. The aircraft of claim 9, wherein in the staggered configuration, compressors of the at least two first engines are axially offset and compressors of the at least two second engines are axially offset. 11. The aircraft of claim 4, wherein the fuselage comprises a higher portion and a lower portion, and wherein the first and second fixed wings are coupled to and extend from the lower portion of the fuselage. 12. A vertical-lift aircraft, comprising: a fuselage comprising a higher portion and a lower portion;two fixed wings coupled to and extending from opposing sides of the lower portion of the fuselage;two tilt-rotor assemblies each coupled to a respective one of the two fixed wings wherein: each of the tilt-rotor assemblies comprise blades, rotatable about a common plane of rotation;each of the tilt-rotor assemblies is rotatable, relative to the two low fixed wings, respectively, between a vertical orientation, in which the common plane of rotation is a horizontal plane, and a horizontal orientation, in which the common plane of rotation is a vertical plane, perpendicular to the horizontal plane; andthe blades of each of the two tilt-rotor assemblies rotate about the horizontal plane, to generate the entire lift and no forward thrust of the aircraft, and about the vertical plane, to generate the entire forward thrust and no lift of the aircraft;at least two engines non-movably coupled to each of the two fixed wings; anda power transmission system configured to transmit power generated by each of the at least two engines, non-movably coupled to each of the two fixed wings, to both of the two tilt-rotor assemblies, wherein the power transmission system comprises: a mid-wing gearbox positioned within the fuselage between the two fixed wings;a first driveshaft that extends between the mid-wing gearbox and a first of the tilt-rotor assemblies and a second driveshaft that extends between the mid-wing gearbox and a second of the tilt-rotor assemblies, wherein the mid-wing gearbox evenly distributes mechanical rotational energy between the first and second driveshafts at least while all of the at least two engines, non-movably coupled to each of the two fixed wings, are operable; andat least four driveshaft gearboxes coupled to the two fixed wings, wherein each of the at least four driveshaft gearboxes is in power receiving communication with a respective one of the at least two engines, coupled to each of the two fixed wings, and each of the at least four driveshaft gearboxes evenly distributes mechanical rotational energy from the respective one of the at least two engines, coupled to each of the two fixed wings, to respective sections of one of the first and second driveshafts coupled with each of the at least four driveshaft gearboxes. 13. The aircraft of claim 12, wherein each of the two tilt-rotor assemblies is coupled to a tip of the respective one of the two fixed wings. 14. The aircraft of claim 12, wherein the aircraft is a commercial passenger aircraft. 15. A method for operating an aircraft, comprising: providing a tilt-rotor, vertical-lift aircraft comprising two low fixed wings and two tilt-rotor assemblies each rotatably coupled to a respective one of the two low fixed wings, wherein the vertical-lift aircraft further comprises: at least four stationary engines, wherein two of the at least four stationary engines are coupled to each of the two low fixed wings at locations on the two low fixed wings away from the tilt-rotor assemblies;a common power transmission system, operatively coupling the tilt-rotor assemblies to the at least two stationary engines coupled to each of the two low fixed wings, wherein the common power transmission system comprises: a mid-wing gearbox positioned between the two low fixed wings;a first driveshaft that extends between the mid-wing gearbox and a first of the tilt-rotor assemblies and a second driveshaft that extends between the mid-wing gearbox and a second of the tilt-rotor assemblies; andat least four driveshaft gearboxes coupled to the two fixed wings away from the tilt-rotor assemblies;wherein each of the two tilt-rotor assemblies comprise blades, rotatable about a common plane of rotation, and wherein rotation of the first and second driveshafts rotates the blades of the first and second of the tilt-rotor assemblies, respectively;evenly distributing mechanical rotational energy from each stationary engine to respective sections of one of the first and second driveshafts via a respective one of the at least four driveshaft gearboxes; andevenly distributing mechanical rotational energy between the first and second driveshafts at least while all of the at least two stationary engines, coupled to each of the two low fixed wings, are operable.

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Cedoz, Robert W.. Aircraft with counter-rotating turbofan engines. USP2018019878798.

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[특허] Purebred and hybrid electric VTOL tilt rotor aircraft 함께 이용한 콘텐츠

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Tilt-rotor vertical-lift aircraft

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