[특허]Long endurance vertical takeoff and landing aircraft

DZYNE Technologies, Inc.

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특허 상세정보

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내보내기 페이스북 공유 트위터 공유 카카오톡 공유

Long endurance vertical takeoff and landing aircraft

특허상세정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	B64C-029/02 B64C-039/02
미국특허분류(USC)	244/078; 244/039; 244/056
출원번호	US-0429156 (2012-03-23)
등록번호	US-8991751 (2015-03-31)
발명자 / 주소	Page, Mark Allan McCue, Matthew Robert Godlasky, Robert Anthony
출원인 / 주소	DZYNE Technologies, Inc.
대리인 / 주소	Tsircou Law P.C.
인용정보	피인용 횟수 : 10 인용 특허 : 3

초록
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An aircraft for use in fixed wing flight mode and rotor flight mode is provided. The aircraft can include a fuselage, wings, and a plurality of engines. The fuselage can comprise a wing attachment region further comprising a rotating support. A rotating section can comprise a rotating support and the wings, with a plurality of engines attached to the rotating section. In a rotor flight mode, the rotating section can rotate around a longitudinal axis of the fuselage providing lift for the aircraft similar to the rotor of a helicopter. In a fixed wing flight mode, the rotating section does not rotate around a longitudinal axis of the fuselage, providing lift for the aircraft similar to a conventional airplane. The same engines that provide torque to power the rotor in rotor flight mode also power the aircraft in fixed wing flight mode.

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청구항
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1. An aircraft capable of fixed wing and rotor flight modes wherein a fixed wing flight mode is defined as flight in which aircraft wings are rotationally stationary about a fuselage and a rotor flight mode is defined as flight in which aircraft wings rotate about the fuselage, the aircraft comprising: a plurality of wings including a first wing and a second wing, each wing having a spar such that each wing is rotatable about a span-wise axis defined by said spar;at least one actuator coupled to the spar of each of the plurality of wings;a plurality of engines secured to said wings, including a first engine secured to said first wing at a position between 20% and 75% of semi-span of said first wing and a second engine secured to said second wing at a position between 20% and 75% of semi-span of said second wing;the fuselage further comprising a rotating support coupled to said plurality of wings to rotate said wings about a longitudinal axis of the fuselage in a rotor flight mode and to maintain said wings rotationally stationary relative to the longitudinal axis of the fuselage in a fixed wing flight mode; andfuel tanks disposed in the wings and operatively coupled to the plurality of engines. 2. The aircraft of claim 1, wherein the plurality of engines are each solely confined to the wings such that the fuselage is free of structure that contributes to generating motive force of any of the plurality of engines. 3. The aircraft of claim 2, wherein said engines exclusively provide motive force to power flight in both fixed wing flight mode and rotor flight mode. 4. The aircraft of claim 1, wherein each wing includes a rear swept portion proximate to the fuselage and a forward swept portion distal to the rear swept portion. 5. The aircraft of claim 4, wherein the first engine is disposed between the rear swept portion and the forward swept portion of the first wing, and the second engine is disposed between the rear swept portion and the forward swept portion of the second wing. 6. The aircraft of claim 1, further comprising a plurality of tail stabilizing surfaces. 7. The aircraft of claim 6, wherein said plurality of tail stabilizing surfaces further comprise at least one control surface for controlling the orientation of the aircraft when the aircraft is flying in fixed wing mode or in rotor flight mode. 8. The aircraft of claim 1, wherein each of the plurality of engines are secured to a corresponding wing of the plurality of wings at a prescribed semi-span distance that is disposed at or between a first calculated location and a second calculated location, in which (a) the first calculated location is a location along the semi-span calculated to optimize rotor flight mode for the corresponding wing and propulsive power of the corresponding engine,(b) the second calculated location is a location along the semi-span calculated to optimize fixed wing flight mode for the corresponding wing and propulsive power of the corresponding engine, and(c) the first calculated location and the second calculated location are no more than 25% apart along of the semi-span distance. 9. An aircraft capable of fixed wing and rotor flight modes, comprising: a fuselage main body defining a longitudinal axis, the fuselage main body having a nose section, tail section, and wing attachment section disposed between the nose section and the tail section;a plurality of dual-purpose wings, including a first wing and a second wing, rotatably mounted to said wing attachment section of fuselage for a fixed wing flight mode and for a rotor flight mode, in which the fixed wing flight mode is defined as flight in which said wings are maintained rotationally stationary relative to the longitudinal axis and the rotor flight mode is defined as flight in which said wings rotate about the longitudinal axis, each wing having an actuated spar coupled to said wing attachment section such that each wing is rotatable about a span-wise axis defined by said spar;a plurality of engines, including a first engine secured to said first wing at a position spaced proximally from a wing tip of said first wing and a second engine a position spaced proximally from a wing tip of said second wing, the plurality of engines are each solely confined to the wings such that the fuselage is free of structure that contributes to generating motive force of any of the plurality of engines; andfuel tanks disposed in the wings and operatively coupled to the plurality of engines. 10. The aircraft of claim 9, wherein each of the plurality of engines are secured to a corresponding wing of the plurality of wings at a prescribed semi-span distance that is disposed at or between a first calculated location and a second calculated location, in which (a) the first calculated location is a location along the semi-span calculated to optimize rotor flight mode for the corresponding wing and propulsive power of the corresponding engine,(b) the second calculated location is a location along the semi-span calculated to optimize fixed wing flight mode for the corresponding wing and propulsive power of the corresponding engine, and(c) the first calculated location and the second calculated location are no more than 25% apart along of the semi-span distance. 11. The aircraft of claim 9, wherein each wing includes a rear swept portion proximate to the fuselage and a forward swept portion distal to the rear swept portion. 12. The aircraft of claim 11, wherein the first engine is disposed between the rear swept portion and the forward swept portion of the first wing, and the second engine is disposed between the rear swept portion and the forward swept portion of the second wing. 13. The aircraft of claim 9, further comprising a plurality of tail stabilizing surfaces. 14. The aircraft of claim 13, wherein said plurality of tail stabilizing surfaces further comprise at least one control surface for controlling the orientation of the aircraft when the aircraft is flying in fixed wing mode or in rotor flight mode. 15. An aircraft capable of fixed wing and rotor flight modes, comprising: a fuselage main body defining a longitudinal axis, the fuselage main body having a nose section, tail section, and wing attachment section disposed between the nose section and the tail section;a plurality of dual-purpose wings, including a first wing and a second wing, rotatably mounted to said wing attachment section of fuselage for a fixed wing flight mode and for a rotor flight mode, in which the fixed wing flight mode is defined as flight in which said wings are maintained rotationally stationary relative to the longitudinal axis and the rotor flight mode is defined as flight in which said wings rotate about the longitudinal axis, each wing having an actuated spar coupled to said wing attachment section such that each wing is rotatable about a span-wise axis defined by said spar;a plurality of engines, wherein each of the plurality of engines are secured to a corresponding wing of the plurality of wings at a prescribed semi-span distance that is disposed at or between a first calculated location and a second calculated location, in which (a) the first calculated location is a location along the semi-span calculated to optimize rotor flight mode for the corresponding wing and propulsive power of the corresponding engine,(b) the second calculated location is a location along the semi-span calculated to optimize fixed wing flight mode for the corresponding wing and propulsive power of the corresponding engine, and(c) the first calculated location and the second calculated location are no more than 25% apart along of the semi-span distance; andfuel tanks disposed in the wings and operatively coupled to the plurality of engines. 16. The aircraft of claim 15, wherein the plurality of engines are each solely confined to the wings such that the fuselage is free of structure that contributes to generating motive force of any of the plurality of engines. 17. The aircraft of claim 16, wherein said engines exclusively provide motive force to power flight in both fixed wing flight mode and rotor flight mode. 18. The aircraft of claim 15, wherein each wing includes a rear swept portion proximate to the fuselage and a forward swept portion distal to the rear swept portion. 19. The aircraft of claim 18, wherein the first engine is disposed between the rear swept portion and the forward swept portion of the first wing, and the second engine is disposed between the rear swept portion and the forward swept portion of the second wing. 20. The aircraft of claim 15, further comprising a plurality of tail stabilizing surfaces. 21. The aircraft of claim 20, wherein said plurality of tail stabilizing surfaces further comprise at least one control surface for controlling the orientation of the aircraft when the aircraft is flying in fixed wing mode or in rotor flight mode. 22. The aircraft of claim 15, wherein the wings are symmetric airfoils. 23. The aircraft of claim 15, wherein said engines may be jet engines or propeller engines.

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이 특허를 인용한 특허 피인용횟수: 10

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Long endurance vertical takeoff and landing aircraft

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Long endurance vertical takeoff and landing aircraft

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