[특허]Winglet system and method

Winglet system and method 원문보기

IPC분류정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	B64C-023/06
출원번호	US-0566483 (2014-12-10)
등록번호	US-9216817 (2015-12-22)
발명자 / 주소	Roman, Dino L. Vassberg, John C. Friedman, Douglas M. Malachowski, Adam P. Vegter, Christopher A.
출원인 / 주소	The Boeing Company
인용정보	피인용 횟수 : 0 인용 특허 : 45

초록 ▼

A winglet system for an aircraft wing may include an upper winglet and a lower winglet mounted to a wing tip. The lower winglet may have a static position when the wing is subject to an on-ground static loading. The lower winglet may be configured such that upward deflection of the wing under an approximate 1-g flight loading causes the lower winglet to move upwardly and outwardly from the static position to an in-flight position resulting in an effective span increase of the wing under the approximate 1-g flight loading relative to the span of the wing under the on-ground static loading. The lower winglet may have a length of approximately 50-80 percent of a length of the upper winglet.

대표청구항 ▼

1. A winglet system, comprising: an upper winglet and a lower winglet mounted to a wing;the lower winglet has a length of approximately 50-80 percent of a length of the upper winglet;the lower winglet having a static position when the wing is subject to an on-ground static loading; andthe lower winglet being configured such that upward deflection of the wing under an approximate 1-g flight loading causes the lower winglet to move upwardly and outwardly from the static position to an in-flight position resulting in an effective span increase of the wing under the approximate 1-g flight loading relative to the span of the wing under the on-ground static loading. 2. The winglet system of claim 1 wherein: the lower winglet is oriented at an anhedral angle of no less than approximately 15 degrees during the upward deflection of the wing under the approximate 1-g flight loading. 3. The winglet system of claim 1 wherein: the upper winglet is oriented at a dihedral angle of at least approximately 60 degrees during upward deflection of the wing under the approximate 1-g flight loading. 4. The winglet system of claim 1, wherein: an upper winglet tip and a lower winglet tip terminate at approximately the same lateral location when the wing is under the on-ground static loading. 5. The winglet system of claim 1 wherein: the lower winglet has a center of pressure;the wing having a wing torsional axis; andthe center of pressure of the lower winglet being located aft of the wing torsional axis. 6. The winglet system of claim 1, wherein: the wing has a wing tip including a wing tip chord;the upper winglet and the lower winglet each having a root chord; andthe upper winglet root chord and the lower winglet root chord each having a length of at least approximately 50 percent of the wing tip chord. 7. The winglet system of claim 6, wherein: the upper winglet root chord and the lower winglet root chord each have a length of from approximately 60 to 100 percent of a length of the wing tip chord. 8. The winglet system of claim 1, wherein: at least one of the upper winglet and lower winglet has a leading edge root glove mounted at a juncture of a wing tip with the respective upper winglet and lower winglet. 9. The winglet system of claim 1, wherein: the upper winglet and the lower winglet each have a taper ratio of tip chord to root chord in a range of from approximately 0.15 to 0.50. 10. The winglet system of claim 1, wherein: the upper winglet and the lower winglet have a leading edge sweep angle of between approximately 20 and 70 degrees. 11. The winglet system of claim 1, wherein: the wing has a wing torsional axis;the upper winglet and the lower winglet having a combined winglet area and a combined center of gravity located at a longitudinal offset from the wing torsional axis; andthe upper winglet and lower winglet being configured such that the longitudinal offset is less than a longitudinal offset of a center of gravity of a single upper winglet having a winglet area that is substantially equivalent to the combined winglet area and having a leading edge sweep angle that is substantially equivalent to the upper winglet leading edge sweep angle. 12. An aircraft, comprising: a pair of wings each having a wing tip;an upper winglet and a lower winglet mounted to each one of the wing tips;the lower winglet having a static position when the wing is subject to an on-ground static loading;the lower winglet having a length of approximately 50-80 percent of a length of the upper winglet; andthe lower winglet being sized and oriented such that upward deflection of the wings under an approximate 1-g flight loading causes the lower winglet to move upwardly and outwardly from the static position to an in-flight position resulting in an effective span increase of the wing under the approximate 1-g flight loading relative to the span of the wing under an on-ground static loading. 13. A method of enhancing performance of an aircraft, comprising the steps of: providing an upper winglet and a lower winglet on a wing, the lower winglet having a static position when the wing is subject to an on-ground static loading, the lower winglet having a length of approximately 50-80 percent of a length of the upper winglet;upwardly deflecting the wing under an approximate 1-g flight loading;moving the lower winglet upwardly and outwardly from the static position to an in-flight position during upward deflection of the wing; andcausing an effective span increase of the wing under the approximate 1-g flight loading relative to the span of the wing under the on-ground static loading in response to moving the lower winglet upwardly and outwardly from the static position to the in-flight position. 14. The method of claim 13, further comprising the step of: orienting the lower winglet at an anhedral angle of no less than approximately 15 degrees during the upward deflection of the wing under the approximate 1-g flight loading. 15. The method of claim 13, further comprising the step of: orienting the upper winglet at a dihedral angle of at least approximately 60 degrees during the upward deflection of the wing under the approximate 1-g flight loading. 16. The method of claim 13, wherein: an upper winglet tip and a lower winglet tip terminate at approximately the same lateral location when the wing is under the on-ground static loading. 17. The method of claim 13, further comprising the steps of: locating the lower winglet such that a center of pressure is aft of a wing torsional axis;increasing lift of the lower winglet during a gust load; andexerting a nose-down moment on a wing tip in response to an increase in the lift of the lower winglet. 18. The method of claim 17, further comprising the step of: dividing a wing tip aerodynamic load between the upper winglet and the lower winglet, the upper winglet and the lower winglet each having a root chord having a length of at least approximately 50 percent of a wing tip chord. 19. The method of claim 18, further comprising the step of: minimizing parasitic drag of the aircraft by using a leading edge root glove on at least one of the upper winglet and the lower winglet. 20. The method of claim 18, further comprising the steps of: providing the upper winglet and the lower winglet with a combined winglet area and a combined center of gravity that is longitudinally offset from a wing torsional axis; andreducing wing flutter by longitudinally offsetting the combined center of gravity by an amount that is less than a longitudinal offset of a center of gravity of a single upper winglet having a winglet area that is substantially equivalent to the combined winglet area and having a leading edge sweep angle that is substantially equivalent to the upper winglet leading edge sweep angle.

이 특허에 인용된 특허 (45)

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IPC	Description
A	생활필수품
A62	인명구조; 소방(사다리 E06C)
A62B	인명구조용의 기구, 장치 또는 방법(특히 의료용에 사용되는 밸브 A61M 39/00; 특히 물에서 쓰이는 인명구조 장치 또는 방법 B63C 9/00; 잠수장비 B63C 11/00; 특히 항공기에 쓰는 것, 예. 낙하산, 투출좌석 B64D; 특히 광산에서 쓰이는 구조장치 E21F 11/00)
A62B-1/08	.. 윈치 또는 풀리에 제동기구가 있는 것

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