Aircraft wing composed of composite and metal panels
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
B64C-003/20
B64C-003/00
출원번호
US-0027570
(2004-12-29)
등록번호
US-7387277
(2008-06-17)
발명자
/ 주소
Kordel,Jan A.
Tanner,Richard B.
Burford,Ian C.
Munsen,Victor A.
McGinty,Daniel E.
Rampton,Scott N.
Fox,Bruce R.
Kelly,James M.
Johnson,Miles O.
출원인 / 주소
The Boeing Company
대리인 / 주소
Lee & Hayes, PLLC
인용정보
피인용 횟수 :
8인용 특허 :
21
초록▼
Aircraft wing assemblies having both composite and metal panels are disclosed. In one embodiment, a wing assembly includes a support structure, an upper panel assembly formed from a metal material and coupled to the support structure, and a lower panel assembly formed from a composite material and c
Aircraft wing assemblies having both composite and metal panels are disclosed. In one embodiment, a wing assembly includes a support structure, an upper panel assembly formed from a metal material and coupled to the support structure, and a lower panel assembly formed from a composite material and coupled to the support structure. The metal material may be aluminum, titanium, or any other suitable metal, and the composite material may be a carbon fiber reinforced plastic (CFRP) material or other suitable composite material. In another embodiment, the upper panel assembly includes a downwardly depending first web portion, and the lower panel assembly includes an upwardly depending second web portion, the second web portion being proximate the first web portion, and an interface member of an isolating material is disposed between the first and second web portions.
대표청구항▼
What is claimed is: 1. A wing assembly for use on an aircraft, comprising: a support structure having a first end portion configured to be coupled to the aircraft; an upper panel assembly formed from a metal material and coupled to the support structure; a lower panel assembly formed from a composi
What is claimed is: 1. A wing assembly for use on an aircraft, comprising: a support structure having a first end portion configured to be coupled to the aircraft; an upper panel assembly formed from a metal material and coupled to the support structure; a lower panel assembly formed from a composite material and coupled to the support structure; and wherein the upper panel assembly includes a downwardly depending first web portion positioned proximate the first end portion of the support structure, and the lower panel assembly includes an upwardly depending second web portion, the second web portion being proximate the first web portion, the wing assembly further comprising an interface member of an isolating material disposed between the first and second web portions, and at least one fastener coupling the second web portion, the interface member, and the first web portion to the support structure. 2. The wing assembly of claim 1, wherein the metal material includes at least one of aluminum and titanium, and wherein the composite material includes a carbon fiber reinforced plastic (CFRP) material. 3. The wing assembly of claim 1, further comprising a rib member extending along and coupled to at least one of the first and second web portions. 4. The wing assembly of claim 1, wherein the upper panel assembly includes an upper spar chord proximate the first end of the support structure, the first web portion being a portion of the upper spar chord, and wherein the lower panel assembly includes a lower spar chord, the second web portion being a portion of the lower spar chord. 5. The wing assembly of claim 1, wherein the upper panel assembly includes a first skin coupled to the support structure by a plurality of first web members, and the lower panel assembly includes a second skin coupled to the support structure by a plurality of second web members. 6. The wing assembly of claim 1, further comprising at least one fillet seal disposed on at least one edge portion of at least one of the first and second web portions. 7. The wing assembly of claim 1, wherein the interface member is formed of a fiberglass isolating ply material. 8. The wing assembly of claim 1, wherein the interface member is formed of a material that prevents galvanic corrosion of the upper panel assembly. 9. The wing assembly of claim 1, wherein the downwardly depending first web portion is coated with one or more coats of a non-electrically conducting material. 10. A wing assembly for use on an aircraft, comprising: a support structure having a first end portion configured to be coupled to the aircraft; an upper panel assembly coupled to an upper portion of the support structure and having a downwardly-depending member formed from a metal material; a lower panel assembly coupled to a lower portion of the support structure and having an upwardly-depending member formed from a composite material, the upwardly-depending member being coupled to the downwardly-depending member; and at least one interface member disposed between the downwardly-depending member and the upwardly-depending member. 11. The wing assembly of claim 10, wherein the metal material includes at least one of aluminum and titanium, and wherein the composite material includes a carbon fiber reinforced plastic (CFRP) material. 12. The wing assembly of claim 10, wherein the upper panel assembly is formed entirely from a metal material. 13. The wing assembly of claim 10, wherein the lower panel assembly is formed entirely from a composite material. 14. The wing assembly of claim 10, wherein the at least one interface member is formed of a non-conductive material. 15. A wing assembly for use on an aircraft, comprising: a support structure having a first end portion adapted to be coupled to the aircraft; an upper panel assembly having an upper skin coupled to the support structure and including a downwardly depending first web portion positioned proximate the first end portion of the support structure, the first web portion being formed from a metal material; a lower panel assembly having a lower skin coupled to the support structure and including an upwardly depending second web portion formed from a composite material, the second web portion being proximate the first web portion; an interface member of an isolating material disposed between the first and second web portions; and at least one fastener coupling the second web portion, the interface member, and the first web portion to the support structure. 16. The wing assembly of claim 15, wherein the metal material includes at least one of aluminum and titanium, and wherein the composite material includes a carbon fiber reinforced plastic (CFRP) material. 17. The wing assembly of claim 15, wherein the upper panel assembly is formed entirely from a metal material. 18. The wing assembly of claim 15, wherein the lower panel assembly is formed entirely from a composite material. 19. The wing assembly of claim 15, further comprising at least one fillet seal disposed on at least one edge portion of at least one of the first and second web portions. 20. The wing assembly of claim 15, wherein the interface member is formed of a fiberglass isolating ply material. 21. An aircraft, comprising: a fuselage having an airframe; a propulsion system operatively coupled to at least one of the fuselage and the airframe; and at least one wing assembly including: a support structure having a first end portion coupled to at least one of the fuselage and the airframe; an upper panel assembly coupled to an upper portion of the support structure and having a downwardly-depending member formed from a metal material; a lower panel assembly coupled to a lower portion of the support structure and having an upwardly-depending member formed from a composite material, the upwardly-depending member being coupled to the downwardly-depending member; and wherein the upper panel assembly includes the downwardly depending member positioned proximate the first end portion of the support structure and the lower panel assembly includes the upwardly depending member, the upwardly depending member being proximate the downwardly depending member, the wing assembly further comprising an interface member of an isolating material disposed between the upwardly depending member and the downwardly depending member, and at least one fastener coupling the downwardly depending member, the interface member, and the upwardly depending member to the support structure. 22. The aircraft of claim 21, wherein the metal material includes at least one of aluminum and titanium, and wherein the composite material includes a carbon fiber reinforced plastic (CFRP) material. 23. The aircraft of claim 21, wherein the upper panel assembly includes an upper spar chord proximate the first end of the support structure, the first web portion being a portion of the upper spar chord, and wherein the lower panel assembly includes a lower spar chord, the second web portion being a portion of the lower spar chord. 24. The aircraft of claim 21, wherein the interface member is formed of a fiberglass isolating ply material. 25. The aircraft of claim 21, wherein the support structure is formed of a metal material.
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