Integrated wingtip extensions for jet transport aircraft and other types of aircraft
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
B64C-023/06
B64C-009/00
출원번호
US-0187443
(2005-07-21)
등록번호
US-8544800
(2013-10-01)
발명자
/ 주소
Stuhr, Victor K.
출원인 / 주소
The Boeing Company
인용정보
피인용 횟수 :
8인용 특허 :
42
초록▼
Methods and systems for efficiently increasing the wing area of an aircraft are disclosed herein. An integrated wingtip extension configured in accordance with one embodiment of the invention includes a tapered wing section and a winglet. The tapered wing section includes an inboard end portion havi
Methods and systems for efficiently increasing the wing area of an aircraft are disclosed herein. An integrated wingtip extension configured in accordance with one embodiment of the invention includes a tapered wing section and a winglet. The tapered wing section includes an inboard end portion having a first chord length and an outboard end portion having a second chord length that is less than the first chord length. The winglet is fixedly attached to the outboard end portion. The inboard end portion is configured to be fixedly attached to a tip portion of an aircraft wing. In one embodiment, the tapered wing section and the winglet can be integrally formed from composite materials.
대표청구항▼
1. An aircraft system comprising: a baseline aircraft main wing having a trailing edge control surface and a distal tip portion spaced apart from a root portion, the distal tip portion being configured to be attached to a first winglet; anda unitary wingtip extension comprising: a tapered wing secti
1. An aircraft system comprising: a baseline aircraft main wing having a trailing edge control surface and a distal tip portion spaced apart from a root portion, the distal tip portion being configured to be attached to a first winglet; anda unitary wingtip extension comprising: a tapered wing section having an inboard end portion with a first chord length and an outboard end portion with a second chord length that is less than the first chord length, the inboard end portion being fixedly attached to the distal tip portion of the baseline aircraft main wing; anda second winglet extending from the outboard end portion of the tapered wing section;the tapered wing section including a trailing edge control surface operably coupled to the trailing edge control surface of the baseline aircraft main wing. 2. The aircraft system of claim 1 wherein the outboard end portion of the tapered wing section is spaced apart from the inboard end portion of the tapered wing section by a spanwise dimension that is at least as long as the second chord length. 3. The aircraft system of claim 1 wherein the tapered wing section further includes a first trailing edge portion and the baseline aircraft main wing further includes a second trailing edge portion, and wherein the first trailing edge portion is configured to be aligned with the second trailing edge portion when the inboard end portion of the tapered wing section is fixedly attached to the distal tip portion of the baseline aircraft main wing. 4. The aircraft system of claim 1 wherein the tapered wing section further includes a first leading edge portion and a first trailing edge portion, wherein the baseline aircraft main wing further includes a second leading edge portion and a second trailing edge portion, and wherein the first leading edge portion is configured to be aligned with the second leading edge portion, and the first trailing edge portion is configured to be aligned with the second trailing edge portion, when the inboard end portion of the tapered wing section is fixedly attached to the distal tip portion of the baseline aircraft main wing. 5. The aircraft system of claim 1 wherein the tapered wing section further includes a first leading edge portion and a first trailing edge portion, wherein the baseline aircraft main wing further includes a second leading edge portion and a second trailing edge portion, and wherein the first leading edge portion of the tapered wing section is configured to sweep aft of the second leading edge portion of the baseline aircraft main wing, and the first trailing edge portion of the tapered wing section is configured to sweep aft of the second trailing edge portion of the baseline aircraft main wing, when the inboard end portion of the tapered wing section is fixedly attached to the tip portion of the baseline aircraft main wing. 6. The aircraft system of claim 1 wherein the tapered wing section further includes a first leading edge control surface and the baseline aircraft main wing further includes a second leading edge control surface, and wherein the first leading edge control surface is configured to be operably coupled to the second leading edge control surface when the inboard end portion of the tapered wing section is fixedly attached to the tip portion of the baseline aircraft main wing. 7. The aircraft system of claim 1 wherein the trailing edge control surface of the tapered wing section comprises a first trailing edge control surface and the trailing edge control surface of the baseline aircraft main wing comprises a second trailing edge control surface, and wherein the first trailing edge control surface is configured to be operably coupled to the second trailing edge control surface when the inboard end portion of the tapered wing section is fixedly attached to the tip portion of the baseline aircraft main wing. 8. The aircraft system of claim 1 wherein the tapered wing section further includes a first leading edge control surface, and the trailing edge control surface of the tapered wing section comprises a first trailing edge control surface, wherein the baseline aircraft main wing further includes a second leading edge control surface, and the trailing edge control surface of the baseline aircraft main wing comprises a second trailing edge control surface, and wherein the first leading edge control surface is configured to be operably coupled to the second leading edge control surface, and the first trailing edge control surface is configured to be operably coupled to the second trailing edge control surface, when the inboard end portion of the tapered wing section is fixedly attached to the tip portion of the baseline aircraft main wing. 9. The aircraft system of claim 1 wherein the tapered wing section further includes a first navigation light system and the baseline aircraft main wing further includes a second navigation light system, and wherein the first navigation light system is configured to be operably connected to the second navigation light system when the inboard end portion of the tapered wing section is fixedly attached to the tip portion of the baseline aircraft main wing. 10. The aircraft system of claim 1 wherein the tapered wing section and the second winglet are integrally formed from composite materials. 11. The aircraft system of claim 1: wherein the tapered wing section and the second winglet are integrally formed from composite materials;wherein the tapered wing section further includes a first leading edge portion, a first trailing edge portion, a first leading edge control surface, and a first light system, and wherein the trailing edge control surface comprises a first trailing edge control surface;wherein the baseline aircraft main wing further includes a second leading edge portion, a second trailing edge portion, a second leading edge control surface, and a second light system, and wherein the trailing edge control surface comprises a second trailing edge control surface; andwherein the first leading edge portion of the tapered wing section is configured to be aligned with the second leading edge portion of the baseline aircraft main wing, the first trailing edge portion of the tapered wing section is configured to be aligned with the second trailing edge portion of the baseline aircraft main wing, the first leading edge control surface is configured to be operably coupled to the second leading edge control surface, the first trailing edge control surface is configured to be operably coupled to the second trailing edge control surface, and the first light system is configured to be operably connected to the second light system when the inboard end portion of the tapered wing section is fixedly attached to the tip portion of the baseline aircraft main wing. 12. A derivative aircraft system comprising: a baseline main wing from a baseline aircraft, the baseline main wing having a trailing edge control surface and a first tip portion spaced apart from a first root portion;a tapered wing section having a second tip portion spaced apart from a second root portion, the second root portion having a first chord length and the second tip portion having a second chord length that is less than the first chord length;a winglet;means for fixedly attaching the second root portion of the tapered wing section to the first tip portion of the baseline aircraft main wing;means for fixedly attaching the winglet to the second tip portion of the tapered wing section; andthe tapered wing section including a trailing edge control surface operably coupled to the trailing edge control surface of the baseline aircraft main wing. 13. The derivative aircraft system of claim 12 wherein the winglet and the tapered wing section are an integral composite structure. 14. The derivative aircraft system of claim 12 wherein the baseline main wing further includes a first leading edge portion and a first trailing edge portion, wherein the tapered wing section further includes a second leading edge portion and a second trailing edge portion, and wherein the first leading edge portion is configured to be aligned with the second leading edge portion, and the first trailing edge portion is configured to be aligned with the second trailing edge portion, when the second root portion of the tapered wing section is fixedly attached to the first tip portion of the baseline aircraft main wing. 15. The derivative aircraft system of claim 12, further comprising means for operably coupling the movable control surface carried by the baseline aircraft main wing with the movable control surface carried by the tapered wing section. 16. The derivative aircraft system of claim 12, further comprising: means for operably coupling a first leading edge control surface carried by the baseline aircraft main wing with a second leading edge control surface carried by the tapered wing section; and means for operably coupling the trailing edge control surface carried by the baseline aircraft main wing with the trailing edge control surface carried by the tapered wing section. 17. The derivative aircraft system of claim 12 wherein the winglet is a second winglet, and wherein the first tip portion of the baseline aircraft main wing is configured to be fixedly attached to a first winglet. 18. A derivative wing assembly comprising: a baseline aircraft main wing having a first leading edge portion, a first trailing edge portion, and a trailing edge control surface, wherein the baseline aircraft main wing further includes a tip portion configured to be fixedly attached to a first winglet that extends from the tip portion at an angle relative to the baseline aircraft main wing; andan integrated wingtip extension fixedly attached to the tip portion of the baseline aircraft main wing to increase the wing area of the baseline aircraft main wing, wherein the integrated wingtip extension includes: a tapered wing section having an outboard end portion spaced apart from an inboard end portion by a spanwise dimension, wherein the inboard end portion has a first chord length and the outboard end portion has a second chord length that is less than the first chord length, wherein the second chord length is also less than the spanwise dimension, and wherein the tapered wing section further includes a second leading edge portion and a second trailing edge portion, wherein the second leading edge portion is aligned with the first leading edge portion and the second trailing edge portion is aligned with the first trailing edge portion when the inboard end portion of the tapered wing section is fixedly attached to the tip portion of the baseline aircraft main wing;a second winglet extending from the outboard end portion of the tapered wing section; andthe tapered wing section including a trailing edge control surface operably coupled to the trailing edge control surface of the baseline aircraft main wing. 19. The derivative wing assembly of claim 18 wherein the tapered wing section and the second winglet are integrally formed from composite materials.
Herrick Larry L. ; Bays-Muchmore C. Byram ; Hoffman Michael S. ; LeGrand Louis L. ; Ogg Steven S. ; Paul ; Jr. Bernard P. ; Visser Kenneth D. ; Wells Stephen L., Blunt-leading-edge raked wingtips.
Wake Brian E. ; Egolf T. Alan ; Lorber Peter F. ; Landgrebe Anton J., Half-plow vortex generators for rotor blades for reducing blade-vortex interaction noise.
Burnham Robert W. ; Fitzpatrick Michael F. ; Muilenberg Dennis A. ; Schoebelen Joseph K. ; Trollen Laurence B., Multi-service common airframe-based aircraft.
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