IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0597250
(2008-04-21)
|
등록번호 |
US-8322656
(2012-12-04)
|
우선권정보 |
DE-10 2007 019 692 (2007-04-26) |
국제출원번호 |
PCT/EP2008/054820
(2008-04-21)
|
§371/§102 date |
20091023
(20091023)
|
국제공개번호 |
WO2008/132087
(2008-11-06)
|
발명자
/ 주소 |
|
출원인 / 주소 |
|
대리인 / 주소 |
Lerner, David, Littenberg, Krumholz & Mentlik, LLP
|
인용정보 |
피인용 횟수 :
7 인용 특허 :
2 |
초록
▼
A wing-fuselage section of an aircraft, which wing-fuselage section comprises a wing root at which the wing of the aircraft is connected to the fuselage, a fuselage region with fuselage frame elements that extent across the longitudinal direction of the aircraft, and a wing region with spars that ex
A wing-fuselage section of an aircraft, which wing-fuselage section comprises a wing root at which the wing of the aircraft is connected to the fuselage, a fuselage region with fuselage frame elements that extent across the longitudinal direction of the aircraft, and a wing region with spars that extend in the direction of the wingspan. According to the invention, the spars of the wing region and the fuselage frame elements of the fuselage region form part of an integral assembly that extends at least over a middle part of the wing and the fuselage region, including the wing roots.
대표청구항
▼
1. A wing-fuselage section of an aircraft, said wing-fuselage section comprising: a wing root at which a wing of the aircraft is connected to a fuselage;a fuselage region comprising a plurality of fuselage frame elements extending across a longitudinal direction of the aircraft; anda wing region com
1. A wing-fuselage section of an aircraft, said wing-fuselage section comprising: a wing root at which a wing of the aircraft is connected to a fuselage;a fuselage region comprising a plurality of fuselage frame elements extending across a longitudinal direction of the aircraft; anda wing region comprising a plurality of spars that extend in a direction of the wingspan,wherein the spars of the wing region at the wing root continue as a single piece transition in an integral manner in the fuselage frame elements of the fuselage region forming part of an integral assembly that extends at least over a middle part of the wing and the fuselage region, including the wing root, and wherein the spars that extend in the direction of the wingspan of the wing region generally follow a sweep of the wing extending at a non-perpendicular angle to the longitudinal direction of the aircraft, andwherein at least one of the fuselage frame elements intersect with at least one other fuselage frame element in the fuselage region. 2. The wing-fuselage section of claim 1, wherein the integral assembly extends in the longitudinal direction of the aircraft from a front interface that is provided for connecting a front fuselage section to a rear interface that is provided for connecting a rear fuselage section. 3. The wing-fuselage section of claim 1, wherein the integral assembly extends in the direction of the wingspan and comprises at least one interface for connecting an outboard wing to the wing-fuselage section. 4. The wing-fuselage section of claim 1, wherein the integral assembly in the wing region comprises at least one joining region for connecting at least one engine. 5. The wing-fuselage section of claim 4, wherein the joining region for connecting the at least one engine and the interface for connecting the outboard wing are formed by a shared wing connecting element that delimits the integral assembly in the direction of the wingspan. 6. The wing-fuselage structure of claim 1, further comprising at least one carrier element that extends in the longitudinal direction of the aircraft is provided at the wing root, and wherein the spars of the wing region, which spars continue in the fuselage frame elements, on one side extend to the carrier element or on the other side and are connected to said carrier element. 7. The wing-fuselage section of claim 1, wherein the fuselage frame elements form a floor assembly of the fuselage region. 8. The wing-fuselage section of claim 1, wherein the fuselage frame elements form an intermediate-deck carrier structure. 9. The wing-fuselage section of claim 1, wherein the fuselage region defines a circumference, and wherein the fuselage frame elements are configured such that they extend over the entire fuselage circumference. 10. The wing-fuselage section of claim 7, wherein the fuselage frame elements form a unit that integrally comprises the floor assembly and an intermediate-deck carrier structure. 11. The wing-fuselage section of claim 1, wherein the spars or frame elements are formed by a first plurality of continuous structural elements extending in the direction of the wingspan from a first wing region to a second wing region, which structural elements extend between two intersections alternately at the angle of the spar of one side, and at the angle of the spar of the other side, and at the intersections are connected to the continuous structural elements which in each case form the adjacent spars or frame elements which in turn extend between two intersections alternately at the angle of the spar of one side, and at the angle of the spar of the other side, respectively. 12. The wing-fuselage section of claim 11 further comprising in the fuselage region a second plurality of structural elements that supplement the first plurality of structural elements and form part of the fuselage frame elements and that in their extent are limited to the fuselage region. 13. The wing-fuselage section of claim 11, wherein the structural elements are interconnected by a plurality of intersection elements or T-piece elements. 14. The wing-fuselage section of claim 1, wherein at least one of adjacent spars and frame elements are interconnected by ribs that extend in the longitudinal direction of the aircraft. 15. The wing-fuselage section of claim 1, wherein on the spars and frame elements or ribs an outer skin is arranged which, firmly connected to the aforesaid, forms part of the integral assembly. 16. The wing-fuselage section of claim 1, wherein the wing-fuselage section is a metal construction. 17. The wing-fuselage section of claim 1, wherein the wing-fuselage section is a fibre-reinforced plastic construction. 18. The wing-fuselage section of claim 1, wherein the wing-fuselage section is a composite construction. 19. The wing-fuselage section of claim 15, wherein the structural elements comprise fibre fabrics or woven fibre fabrics sewn together at the intersections. 20. The wing-fuselage section of claim 19, wherein the structural elements are reinforced at the intersections by a plurality of intersection elements or T-piece elements. 21. The wing-fuselage section of claim 15, wherein the structural elements comprise fibre fabrics or woven fibre fabrics woven together at the intersections. 22. The wing-fuselage section of claim 21, wherein the structural elements are reinforced at the intersections by a plurality of intersection elements or T-piece elements.
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