IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0308004
(2007-06-06)
|
등록번호 |
US-8695922
(2014-04-15)
|
우선권정보 |
DE-10 2006 026 168 (2006-06-06) |
국제출원번호 |
PCT/EP2007/055556
(2007-06-06)
|
§371/§102 date |
20090514
(20090514)
|
국제공개번호 |
WO2007/141291
(2007-12-13)
|
발명자
/ 주소 |
- Schroeer, Thorsten
- Roming, Thorsten
|
출원인 / 주소 |
|
대리인 / 주소 |
Jenkins, Wilson, Taylor & Hunt, P.A.
|
인용정보 |
피인용 횟수 :
3 인용 특허 :
50 |
초록
▼
An aircraft fuselage structure with frames (11) running transversely with respect to the longitudinal direction of the fuselage, and main deck cross members (14) is disclosed. The aircraft fuselage structure contains premanufactured integral units (10) which each comprise at least the lower region o
An aircraft fuselage structure with frames (11) running transversely with respect to the longitudinal direction of the fuselage, and main deck cross members (14) is disclosed. The aircraft fuselage structure contains premanufactured integral units (10) which each comprise at least the lower region of the fuselage frame (11) and the main deck cross member (14), the fuselage frame (11) and a region (14a) of the main deck cross member (14) that spans at least an essential part of the width of the main deck and merges on both sides into the fuselage frame (11) being premanufactured in the form of an integral component.
대표청구항
▼
1. An aircraft fuselage structure comprising: a plurality of premanufactured integral units, each of which comprises at least a lower region of a fuselage frame that extends transversely with respect to a longitudinal direction of the aircraft fuselage structure, and a main deck cross member,wherein
1. An aircraft fuselage structure comprising: a plurality of premanufactured integral units, each of which comprises at least a lower region of a fuselage frame that extends transversely with respect to a longitudinal direction of the aircraft fuselage structure, and a main deck cross member,wherein the main deck cross member extends over a substantial part of a width of a main deck and merges on both sides into the fuselage frame via supporting elements, which run downwards from the main deck cross member,wherein the supporting elements are arranged offset laterally inwards from the fuselage frame, andwherein the fuselage frame and the main deck cross member that spans a substantial part of the width of the main deck are premanufactured in the form of an integral component before assembly of the aircraft fuselage structure,wherein that part of the main deck cross member which merges via the supporting elements into the fuselage frame ends in a laterally outwards direction at the supporting elements, with a free space that extends from the supporting elements laterally outwards being left open. 2. The aircraft fuselage structure according to claim 1, wherein each of the plurality of premanufactured integral units further comprise a hold cross member which is premanufactured together with the fuselage frame and the main deck cross member in the form of an integral component before assembly of the aircraft fuselage structure. 3. The aircraft fuselage structure according to claim 1, wherein the main deck cross member is joined at its ends to the fuselage frame by side parts which are produced separately and are inserted subsequently, with the free space located outside the supporting elements being spanned. 4. The aircraft fuselage structure according to claim 2, wherein the aircraft fuselage structure is assembled from the plurality of premanufactured integral units, a plurality of skin elements which are connected thereto, and longitudinal members, wherein system lines that are pre-installed in the free space located outside the supporting elements are inserted, and wherein the plurality of premanufactured integral units are fitted into a premanufactured lower partial shell of the aircraft fuselage. 5. The aircraft fuselage structure according to claim 4, wherein the aircraft fuselage structure is assembled from fuselage sections, each of which comprises the plurality of premanufactured integral units. 6. The aircraft fuselage structure according to claim 5, wherein the plurality of premanufactured integral units are produced from web regions situated in the plane of the premanufactured integral unit and from chord regions connected thereto, and wherein the web regions are produced as a single piece with the chord regions, or wherein the chord regions are produced as a separate part in the form of a T-profile and are connected to the web regions. 7. The aircraft fuselage structure according to claim 1, wherein the integral units are produced as a single piece. 8. An integral unit for an aircraft fuselage structure comprising: at least a lower region of a fuselage frame that is configured to extend transversely with respect to a longitudinal direction of the aircraft fuselage structure and a main deck cross member,wherein a portion of the main deck cross member is configured to extend over a substantial part of a width of a main deck and merges on both sides into the fuselage frame via supporting elements, which run downwards from the main deck cross member,wherein the supporting elements are arranged offset laterally inwards from the fuselage frame,wherein the fuselage frame and the portion of main deck cross member that spans a substantial part of the width of the main deck are premanufactured in the form of an integral component before assembly of the aircraft fuselage structure, andwherein that part of the main deck cross member that merges into the fuselage frame via the supporting elements ends or terminates in a laterally outwards direction at the supporting elements, whereby a free space in the laterally outwards direction from the supporting elements is left open. 9. The integral unit according to claim 8, wherein the integral unit further comprises a hold cross member which is premanufactured together with the fuselage frame and the main deck cross member in the form of an integral component before assembly of the aircraft fuselage structure, and wherein the main deck cross member is joined at its ends to the fuselage frame by side parts, which are produced separately and are inserted subsequently, such that the free space located laterally outwards of the supporting elements is spanned, and wherein the integral units are produced as a single piece or from a plurality of parts. 10. The integral unit according to claim 8, wherein the integral unit is produced from web regions situated in the plane of the integral unit and from chord regions connected thereto, and wherein the web regions are produced as a single piece with the chord regions, or wherein the chord regions are produced as a separate part in the form of a T-profile and are connected to the web regions. 11. The integral unit according to claim 8, wherein the integral unit is produced as a single piece. 12. A method for the production of an aircraft fuselage structure comprising: producing a plurality of premanufactured integral units each of which comprises at least a lower region of a fuselage frame and a main deck cross member,wherein a region of the main deck cross member in each of the plurality of premanufactured integral units extends over a substantial part of a width of a main deck of the fuselage structure and merges on both sides into the fuselage frame via supporting elements, which run downwards from the main deck cross member, wherein the supporting elements are arranged offset laterally inwards from the fuselage frame, and wherein the part of the main deck cross member that merges via the supporting elements ends or terminates in a laterally outwards direction at the supporting elements, with a free space in the laterally outwards direction from the supporting elements being left open, and wherein the fuselage frame and the region of the main deck cross member that spans at least a substantial part of the width of the main deck are premanufactured in the form of an integral component before being arranged on an installation apparatus,arranging and adjusting the plurality of premanufactured integral units on an installation apparatus, andjoining the plurality of premanufactured integral units together by longitudinal members. 13. The method according to claim 12, wherein the plurality of premanufactured integral units are each produced with a hold cross member that is premanufactured together with the fuselage frame and the main deck cross member to form an integral component before being arranged on the installation apparatus. 14. The method according to claim 12, wherein the main deck cross member is joined at its ends to the fuselage frame by side parts, which are produced separately and are inserted subsequently, with the free space located laterally outwards of the supporting elements. 15. The method according to claim 12, wherein the aircraft fuselage structure is assembled from the plurality of premanufactured integral units and longitudinal members, and wherein system lines are pre-installed in the free space located laterally outwards of the supporting elements. 16. The method according to claim 13, wherein the aircraft fuselage structure is assembled from the plurality of premanufactured integral units and from a plurality of premanufactured skin elements connected thereto, and wherein the plurality of premanufactured integral units are fitted into a premanufactured lower partial shell of the aircraft fuselage structure. 17. The method according to claim 12 wherein the plurality of premanufactured integral units are produced as a single piece or from a plurality of parts, and wherein the plurality of premanufactured integral units are produced from web regions situated in the plane of the integral unit and from chord regions connected thereto, and wherein the web regions are produced as a single piece with the chord regions, or wherein the chord regions are produced as a separate part in the form of a T-profile and are connected to the web regions. 18. The method according to claim 12, wherein the aircraft fuselage structure is assembled from fuselage sections, each of which comprises a plurality of premanufactured integral units.
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