IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0493843
(2012-06-11)
|
등록번호 |
US-8944386
(2015-02-03)
|
발명자
/ 주소 |
|
출원인 / 주소 |
|
대리인 / 주소 |
|
인용정보 |
피인용 횟수 :
12 인용 특허 :
60 |
초록
▼
A split winglet is disclosed having a first generally upward projecting wing end, and a second generally downward projecting wing end. The second generally downward projecting wing end may be integrally formed with the first generally upward projecting wing end to form a winglet assembly or may be s
A split winglet is disclosed having a first generally upward projecting wing end, and a second generally downward projecting wing end. The second generally downward projecting wing end may be integrally formed with the first generally upward projecting wing end to form a winglet assembly or may be separately attached onto an existing upwardly curved winglet.
대표청구항
▼
1. A wing tip configured to be attached to an attachment end of a wing defining a wing chord plane, comprising: a winglet configured to couple to the attachment end as a continuous extension of the wing, the winglet smoothly transitioning from a continuous extension portion in the wing chord plane t
1. A wing tip configured to be attached to an attachment end of a wing defining a wing chord plane, comprising: a winglet configured to couple to the attachment end as a continuous extension of the wing, the winglet smoothly transitioning from a continuous extension portion in the wing chord plane to a portion extending above the wing chord plane, the winglet including a leading edge swept rearward; anda fin coupled to the winglet, extending below the wing chord plane, the fin having: a leading edge swept rearward, the leading edge including a first curve adjacent the winglet and a second curve adjacent a tip section; anda trailing edge including a third curve adjacent the tip section. 2. The wing tip of claim 1, wherein the winglet has a frontal profile comprising a generally curved transition section continuously extending from the continuous extension portion and a generally linear section continuously extending from the curved transition section. 3. The wing tip of claim 2, wherein the fin projects from the generally curved transition section of the winglet. 4. The wing tip of claim 3, wherein the fin has a generally linear frontal profile. 5. The wing tip of claim 1, wherein the winglet includes a tip section approaching a freestream air direction, and wherein the leading edge is generally linear. 6. The wing tip of claim 5, wherein a trailing edge of the winglet is generally linear. 7. The wing tip of claim 1, wherein the leading edge of the fin includes a generally linear section, and wherein the tip section approaches the freestream air direction. 8. The wing tip of claim 1, wherein a trailing edge of the winglet and the trailing edge of the fin intersect. 9. A wing tip attachable to a wing end, comprising: an upward projecting portion shaped to smoothly and continuously transition from the wing end, the upward projecting portion including a leading edge swept rearward; anda lower projecting portion emanating from a chordwise wing location of the upward projecting portion, the lower projecting portion having: a leading edge swept rearward, the leading edge including a first curve adjacent the upward projecting portion and a second curve adjacent a tip section; anda trailing edge including a third curve adjacent the tip section,wherein the upward projecting portion and the lower projecting portion project outwardly from the wing end. 10. The wing tip of claim 9, wherein the upward projecting portion extends above the wing end and the lower projecting portion extends below the wing end, when the wing tip is attached to the wing end. 11. The wing tip of claim 10, wherein the lower portion projects from the chordwise wing location generally linearly. 12. The wing tip of claim 10, wherein a chord length of the upward projecting portion at the chordwise wing location is greater than a chord length of the lower projecting portion at the chordwise wing location. 13. The wing tip of claim 10 wherein a leading edge of the upward projecting portion approaches the freestream air direction near an end of the upward projecting portion away from the chordwise wing location. 14. The wing tip of claim 9, wherein a transitional section adjacent to the chordwise wing location on the upward projecting portion forms a near-radial curve. 15. The wing tip of claim 14, wherein the upward projecting portion extends generally planar from the transitional section. 16. The wing tip of claim 14, wherein an intersection of the upward projecting portion and lower projecting portion is blended to minimize aerodynamic interference and produce optimal loading. 17. The wing tip of claim 14, wherein the lower portion is a separately attachable fin coupled to an existing curved winglet integrated with an aircraft comprising the upper projecting portion. 18. An aircraft with a wing projecting from a body, the wing having a split wing tip, the split wing tip comprising: a first wing end extending from the wing away from the body along an entire length of the first wing end and projecting above a plane of the wing, the first wing including a leading edge swept rearward; anda second wing end extending from a lower surface of the first wing end and projecting below the plane of the wing, the second wing end having: a leading edge swept rearward, the leading edge including a first curve adjacent the first wing end and a second curve adjacent a tip; anda trailing edge including a third curve adjacent the tip. 19. The aircraft of claim 18, the first wing end further comprising a curved section and a generally planar section, such that the first wing end creates a continuous extension from the plane of the wing through the curved section and upward into the generally planar section, the second wing end projecting generally planar from the curved section. 20. The aircraft of claim 19, wherein the first wing end and the second wing end comprise respective leading edges approaching lines parallel to the longitudinal axis of the aircraft at a first wing end tip and the second wing end tip, respectively. 21. The wing tip of claim 1, wherein the winglet comprises a leading edge configured to align and continuously extend from a leading edge of the wing, and a trailing edge configured to align and continuously extend from a trailing edge of the wing, the leading edge and trailing edge smoothly transitioning through the wing tip. 22. The wing tip of claim 21, wherein the fin trailing edge originates along the trailing edge of the winglet. 23. The wing tip of claim 22, wherein the fin leading edge extends from a lower surface of the winglet such that the fin leading edge does not contact the winglet leading edge. 24. The aircraft of claim 18, wherein the wing comprises a leading edge and a trailing edge smoothly and continuously extending along an entire length from the aircraft body through the first wing end and to a terminal end of the first wing end. 25. The aircraft of claim 24, wherein the leading edge is swept rearward and approaches a line parallel to the longitudinal axis of the aircraft body at the terminal end of the first wing end. 26. The wing tip of claim 1, wherein the winglet comprises an angle between the wing along the wing chord plane and the winglet of generally between 90 degrees and 140 degrees. 27. The wing tip of claim 1, wherein the leading edge of the winglet continuously transitions from a leading edge of the wing. 28. The wing tip of claim 9, wherein the leading edge of the upward projecting portion continuously transitions from a leading edge of the wing end. 29. The aircraft of claim 18, wherein the leading edge of the first wing end continuously transitions from a leading edge of the wing.
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