[특허]Aircraft wing having continuously rotating wing tips

Devenyi, Gabor

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Aircraft wing having continuously rotating wing tips

국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	B64C-023/06 B64C-039/10
출원번호	US-0955639 (2013-07-31)
등록번호	US-9623960 (2017-04-18)
발명자 / 주소	Devenyi, Gabor
출원인 / 주소	Devenyi, Gabor
대리인 / 주소	Reising Ethington P.C.
인용정보	피인용 횟수 : 0 인용 특허 : 14

초록

The present invention relates to a wing for an aircraft. The wing includes a main wing section extending from an inboard end to an outboard end along a lateral axis of the wing, the inboard end for connecting the main wing section to the aircraft. The wing also includes a wing tip having a proximal end and a distal end, the wing tip being rotatably mounted at the proximal end to the outboard end of the main wing section and arranged to freely rotate about a wing tip rotational center with respect to the main wing section.

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1. An aircraft operable to cruise and maneuver through a range of flight speeds comprising: a fuselage extending from a nose end to a tail end along a longitudinal axis; and first and second wings attached to opposing sides of the fuselage, wherein the first and second wings each comprise: a main wing section extending from an inboard end to an outboard end along a lateral axis of the aircraft, the inboard end for connecting the main wing section to the fuselage; andat least one wing tip having a proximal end and a distal end, the at least one wing tip being rotatably mounted at the proximal end to the outboard end of the main wing section and arranged to freely autorotate through at least 360 degrees of motion with respect to the main wing section in response to airflow incident on the at least one wing tip about a wing tip rotational center that is aligned in parallel or coaxially aligned with the mean lift line of the wing. 2. The aircraft according to claim 1, wherein a total surface area of the wing tip is between 2% to 20% of a total surface area of the aircraft wing. 3. The aircraft according to claim 1, wherein a thickness of the wing tip is between 6% to 20% of a median chord length of the wing tip. 4. The aircraft according to claim 1, wherein the wing tip rotational center is arranged proximal to a mean lift line of the main wing section. 5. The aircraft according to claim 4, wherein the wing tip rotational center of at least one wing tip and the mean lift line of the main wing section are coaxially aligned. 6. The aircraft according to claim 1, wherein the main wing section comprises a static wing or fixed wing. 7. The aircraft according to claim 1, further comprising a locking mechanism operable to fix the wing tip to the main wing section in a locked position preventing rotation of the wing tip, and operable to release the wing tip from the locked position where the wing tip is free to rotate about the wing tip rotational center, wherein in the locked position the wing tip is in a feathered position where an incident angle of the wing tip is aligned with the main wing section. 8. The aircraft according to claim 7, wherein the locking mechanism comprises a sliding pin and an associated locking aperture sized to receive the sliding pin. 9. The aircraft according to claim 8, wherein the proximal end of the autorotating wing tip defines the associated locking aperture and the sliding pin extends from and retracts toward the outboard end of the main wing section. 10. The aircraft according to claim 1, further comprising a tubular stub spar extending from the main wing section for each wing tip. 11. The aircraft according to claim 10, further comprising a roller bearing disposed about the tubular stub spar, wherein the proximal end of the wing tip defines a laterally protruding tubular bearing support sized to receive the roller bearing. 12. The aircraft according to claim 11, wherein the tubular stub spar extends through the bearing support, and the roller bearing is interposed between the tubular stub spar and the bearing support to rotatably couple the wing tip to the main wing section. 13. The aircraft according to claim 10, further comprising a drive assembly for rotationally driving the wing tip, the drive assembly comprising a torque motor coupled to a drive shaft which extends from the main wing section through the tubular stub spar and engages the wing tip. 14. The aircraft according to claim 13, further comprising a roller clutch arranged between the drive shaft and the wing tip, the roller clutch being sized to be received by a clutch support housing defined by the distal end of the wing tip, the roller clutch operable for one-way up-driving of the wing tip with respect to the drive shaft so that the wing tip is rotatable in a rotational direction at a speed greater than the rotational speed of the drive shaft. 15. The aircraft according to claim 14, further comprising at least one roller bearing disposed about the drive shaft and interposed between the drive shaft and the tubular stub spar for rotational support of the drive shaft. 16. The aircraft according to claim 15, wherein the torque motor is arranged in the main wing section. 17. The aircraft according to claim 1, further comprising a braking mechanism operable to apply a braking force to stop the autorotation of the wing tip. 18. The aircraft according to claim 17, wherein the braking mechanism is operable to rotate the wing tip to a desired incident angle with respect to the main wing section and return the wing tip to the feathered position where the incident angle of the wing tip is aligned with the main wing section. 19. The aircraft according to claim 18, wherein the braking mechanism is arranged in the wing tip. 20. The aircraft according to claim 1, wherein the autorotation of the wing tip of the first wing and the autorotation rotation of the wing tip of the second wing are mechanically linked to one another. 21. The aircraft according to claim 20, wherein the autorotation of the wing tip of the first wing and the autorotation of the wing tip of the second wing are differentially driven. 22. The aircraft according claim 20, wherein the autorotation of the wing tip of the first wing and the autorotation of the wing tip of the second wing are motor driven independently from one another. 23. The aircraft according to claim 1, wherein the autorotation of the wing tip of the first wing and the autorotation of the wing tip of the second wing are motor driven independently or intermittently from one another. 24. The aircraft according to claim 1, wherein the aircraft is selected from one of a general aviation aircraft, ultra light aircraft, a glider, a compound helicopter and a sailplane. 25. The aircraft according to claim 1, wherein the wing tip of the first wing and the wing tip of the second wing can be reconfigured during flight.

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Aircraft wing having continuously rotating wing tips

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특허 상세정보

Aircraft wing having continuously rotating wing tips

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이 특허에 인용된 특허 (14)

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