Wing leading edge architecture suitable for laminar flow
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
B64C-021/02
B64C-003/14
B64C-009/24
B64C-009/34
B64D-015/04
출원번호
US-0271477
(2014-05-07)
등록번호
US-9896190
(2018-02-20)
발명자
/ 주소
Amorosi, Stephen R.
Santini, Gregory M.
Anderson, Matthew Leroy
Hinrichs, Steve C.
Jarecki, Walter J.
Bennett, Nicholas I.
Pham, Quang Minh
Lai, Paul Hungwai
Rupert, Gregory E.
Osaki, Carl F.
출원인 / 주소
The Boeing Company
대리인 / 주소
Ostranger Chong Flaherty & Broitman P.C.
인용정보
피인용 횟수 :
0인용 특허 :
24
초록▼
A wing leading edge architecture designed to enable laminar flow on passenger jets or other aircraft. The embodiments disclosed herein comprise a metallic fixed leading edge skin panel that is bonded to internal support structure without fasteners except for limited fastening along side edge portion
A wing leading edge architecture designed to enable laminar flow on passenger jets or other aircraft. The embodiments disclosed herein comprise a metallic fixed leading edge skin panel that is bonded to internal support structure without fasteners except for limited fastening along side edge portions adjacent to side edge portions of adjacent leading edge skin panels and along an aft edge portion overlapping a wing skin. In addition, the embodiments disclosed herein integrate a low-drag bleed-air anti-icing (i.e., vent) system and a Krueger flap assembly (e.g., a two-position, high-height, variable-camber Krueger flap assembly).
대표청구항▼
1. A wing assembly comprising: a spar;an upper wing skin joined to said spar, said upper wing skin comprising a forward extension that extends forward of said spar and includes a mating surface offset from a surface of said upper wing skin;a first rib fixedly coupled to and projecting forward from s
1. A wing assembly comprising: a spar;an upper wing skin joined to said spar, said upper wing skin comprising a forward extension that extends forward of said spar and includes a mating surface offset from a surface of said upper wing skin;a first rib fixedly coupled to and projecting forward from said spar;a fixed leading edge skin panel fixedly coupled to said first rib, wherein said fixed leading edge skin panel comprises an upper portion and a lower portion;an upper chord connected to said upper portion of said fixed leading edge skin panel;a lower chord connected to said lower portion of said fixed leading edge skin panel; anda nose beam web fixedly coupled to said upper and lower chords, wherein said first rib is fixedly coupled to said nose beam web,wherein said upper portion of said fixed leading edge skin panel is integrally formed with said lower portion and has an aft edge portion that overlaps and is fastened to said forward extension such that a surface of the fixed leading edge skin panel is level with said surface of said upper wing skin. 2. The wing assembly as recited in claim 1, further comprising a shim disposed between said aft edge portion of said upper portion of said fixed leading edge skin panel and said forward extension of said upper wing skin. 3. The wing assembly as recited in claim 1, further comprising an insert made of polymeric material, said insert being disposed in a space bounded by an aft edge of said aft edge portion of said upper portion of said fixed leading edge skin panel, said forward extension of said upper wing skin, and an offset wall of said upper wing skin. 4. The wing assembly as recited in claim 1, further comprising a clip comprising a vertical portion fixedly coupled to said first rib and a horizontal portion fixedly coupled to said forward extension of said upper wing skin. 5. The wing assembly as recited in claim 1, further comprising a stiffener member fixedly coupled to said first rib and connected to said upper portion of said fixed leading edge skin panel, wherein said stiffener member comprises a web and a flange which meet at an intersection, said flange being tapered on both sides of said intersection. 6. The wing assembly as recited in claim 1, further comprising an upper chord connected to said upper portion of said fixed leading edge skin panel, wherein said upper chord comprises a web and a flange which meet at an intersection, said flange being tapered on both sides of said intersection. 7. The wing assembly as recited in claim 1, further comprising a plurality of vents formed by said lower portion of said fixed leading edge skin panel and said lower chord. 8. The wing assembly as recited in claim 7, wherein said lower chord comprises a plurality of channels, said vents being formed by said channels and opposing portions of said lower portion of said fixed leading edge skin panel. 9. The wing assembly as recited in claim 7, wherein said fixed leading edge skin panel and said nose beam web define a cavity in fluid communication with said vents, said wing assembly further comprising a duct in fluid communication with said cavity for coupling to a source of hot air. 10. The wing assembly as recited in claim 1, further comprising: a second rib fixedly coupled to said spar, to said nose beam web, and to said fixed leading edge skin panel;first and second bridge fittings fixedly coupled to and extending between said first and second ribs; anda Krueger flap assembly pivotably coupled to said first and second ribs, wherein said Krueger flap assembly comprises a movable lower leading edge skin panel and a mechanism that abuts said first bridge fitting when said movable lower leading edge panel is in an extended position and abuts said second bridge fitting when said movable lower leading edge skin panel is in a retracted position. 11. The wing assembly as recited in claim 10, wherein said lower chord has a cutout for clearance with said mechanism of said Krueger flap assembly when said movable lower leading edge skin panel is in said extended position. 12. The wing assembly as recited in claim 1, further comprising first and second pluralities of fasteners disposed along a left side edge and a right side edge, respectively, of said upper portion of said fixed leading edge skin panel, and a third plurality of fasteners disposed along an aft edge of said upper portion of said fixed leading edge skin panel. 13. A wing assembly comprising: a fixed leading edge skin panel comprising upper and lower portions;a bulkhead connected to said upper and lower portions of said fixed leading edge skin panel, wherein said bulkhead and said fixed leading edge skin panel define a cavity forward of said bulkhead, and said bulkhead comprises a lower flange connected to said lower portion of said fixed leading edge skin panel, said lower flange comprising a plurality of channels for venting air from said cavity;a bleed-air duct disposed within the cavity, said bleed-air duct comprising at least one opening;first and second ribs fixedly coupled to said bulkhead; anda Krueger flap assembly pivotably coupled to said first and second ribs, wherein said Krueger flap assembly comprises a movable lower leading edge skin panel having a forward portion that overlaps an aft portion of said lower chord when said movable lower leading edge skin panel is in a retracted position, and a mechanism capable of moving said movable lower leading edge skin panel from said retracted position to an extended position in response to actuation,wherein an aft edge of said lower portion of said fixed leading edge skin panel is separated from a forward edge of said movable lower leading edge skin panel by a gap when said movable lower leading edge skin panel is in said retracted position, said gap being in fluid communication with said plurality of channels. 14. The wing assembly as recited in claim 13, wherein said bulkhead further comprises an upper chord connected to said upper portion of said fixed leading edge skin panel, a lower chord connected to said lower portion of said fixed leading edge skin panel, and a nose beam web fixedly coupled to said upper and lower chords, wherein said lower flange is part of said lower chord. 15. A wing assembly comprising: a spar; first and second ribs fixedly coupled to and projecting forward from said spar; a fixed leading edge skin panel comprising upper and lower portions; an upper chord connected to said upper portion of said fixed leading edge skin panel; a lower chord connected to a lower portion of said fixed leading edge skin panel; a nose beam web fixedly coupled to said upper and lower chords and to said first and second ribs; and means for stiffening said wing assembly, said means for stiffening said wing assembly being connected to said upper portion of said fixed leading edge skin panel and fixedly coupled to said first and second ribs, and a Krueger flap assembly pivotably coupled to said first and second ribs, wherein said Krueger flap assembly comprises: a movable lower leading edge skin panel having a forward portion that overlaps an aft portion of said lower chord when said movable lower leading edge skin panel is in a retracted position; anda mechanism capable of moving said movable lower leading edge skin panel from said retracted position to an extended position in response to actuation. 16. The wing assembly as recited in claim 15, wherein said means for stiffening are made of metal, bonded to said fixed leading edge skin panel, and fastened to said first and second ribs. 17. The wing assembly as recited in claim 15, wherein said means for stiffening are made of honeycomb core, bonded to said fixed leading edge skin panel, and fastened to said first and second ribs. 18. The wing assembly as recited in claim 15, wherein said upper chord comprises a web and a flange which meet at an intersection, said flange being tapered on both sides of said intersection.
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이 특허에 인용된 특허 (24)
Paul Laugt FR, Aircraft airfoil leading edge member equipped with a de-icing device.
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