Fuselage segment and method for manufacturing a fuselage segment
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
B64C-001/06
B64C-001/00
출원번호
US-0623724
(2012-09-20)
등록번호
US-9090328
(2015-07-28)
우선권정보
DE-10 2011 113 806 (2011-09-20)
발명자
/ 주소
Goehlich, Robert Alexander
출원인 / 주소
Airbus Operations GmbH
대리인 / 주소
Jenkins, Wilson, Taylor & Hunt, P.A.
인용정보
피인용 횟수 :
0인용 특허 :
5
초록▼
Provided is a fuselage segment that extends in a longitudinal fuselage segment axis and is closed in a circumferential direction around this longitudinal fuselage segment axis. The fuselage segment features a plurality of shell components for forming a skin of the fuselage segment that respectively
Provided is a fuselage segment that extends in a longitudinal fuselage segment axis and is closed in a circumferential direction around this longitudinal fuselage segment axis. The fuselage segment features a plurality of shell components for forming a skin of the fuselage segment that respectively feature two first shell component edges extending along a longitudinal shell component direction and two second shell component edges extending along a lateral shell component direction. The shell components are respectively connected to at least one adjacent shell component along at least one first shell component edge and along at least one second shell component edge. Methods for manufacturing such a fuselage segment are also provided.
대표청구항▼
1. A fuselage segment that extends in a longitudinal fuselage segment axis and is closed in a circumferential direction around the longitudinal fuselage segment axis, wherein the circumferential direction lies in a reference radial plane, relative to which the longitudinal fuselage segment axis exte
1. A fuselage segment that extends in a longitudinal fuselage segment axis and is closed in a circumferential direction around the longitudinal fuselage segment axis, wherein the circumferential direction lies in a reference radial plane, relative to which the longitudinal fuselage segment axis extends perpendicularly, and wherein the fuselage segment comprises: at least two pluralities of shell components each of which shell components respectively feature two first shell component edges lying opposed to each other and extending along a lateral shell component direction and two second shell component edges lying opposed to each other and extending along a longitudinal shell component direction,wherein the shell components of each plurality of shell components are respectively connected to each other at their first shell component edges such that the respective plurality of shell components forms a ring-shaped skin section of the fuselage segment and has a centerline, which is defined as a connection line of the centers of the shortest distances between the second shell component edges respectively lying opposed to each other, and which forms a closed line which lies in a first radial plane which is inclined with regard to the reference radial plane by at least 5 degrees,wherein at least two ring-shaped skin sections are connected to each other at the second shell component edges of the shell components of the adjacent ring-shaped skin sections. 2. A fuselage segment that extends in a longitudinal fuselage segment axis and is closed in a circumferential direction around a coordinate axis in the form of this longitudinal fuselage segment axis, wherein the circumferential direction lies in a reference radial plane, relative to which the longitudinal fuselage segment axis extends perpendicularly, and wherein the fuselage segment features: a plurality of shell components for forming a skin of the fuselage segment that respectively feature two first shell component edges extending along a lateral shell component direction and two second shell component edges extending along a longitudinal shell component direction, wherein the shell components are respectively connected to at least one adjacent shell component along at least one first shell component edge and to at least one adjacent shell component along at least one second shell component edge, anda support structure, on which each of the shell components is mounted, characterized in that the plurality of shell components is arranged in such a way that the local direction of the first shell component edges, on which two respective adjacent ring shaped skin sections are connected to one another, and/or the local direction of the second shell component edges, on which two respective adjacent ring shaped skin sections are connected to one another, at least sectionally extend at an acute angle to the reference radial plane defined by the longitudinal fuselage segment axis and, at an angle of 30° to 60° relative to the reference radial plane defined by the longitudinal fuselage segment axis. 3. The fuselage segment according to claim 2, characterized in that the fuselage segment features: at least one shell component row that, in order to form the skin of the fuselage segment, is respectively composed of shell components that are arranged behind one another viewed in a longitudinal shell component row direction of the respective shell component row and respectively feature longitudinal shell component edges extending along the longitudinal shell component direction and lateral shell component edges extending transverse thereto, wherein two respective shell components are connected to one another on the lateral shell component edges. 4. The fuselage segment according to claim 3, characterized in that at least two shell component rows of the plurality of shell component rows are at least sectionally connected to one another on longitudinal shell component row edges that are formed by the longitudinal shell component edges of the shell components of the respective shell component row, wherein the longitudinal shell component row direction results as the center line referred to the longitudinal shell component edges of a respective shell component row, and wherein the local direction of the respective center line of the shell component rows respectively extends at an angle of more than 10 degrees and, at an angle between 30° and 60 degrees relative to the reference radial plane defined by the longitudinal fuselage segment axis. 5. The fuselage segment according to claim 2, characterized in that the longitudinal shell component edges of the nominal surface of a plurality of shell components that is developed on the plane extend parallel to one another over at least 80% of the length of the respective longitudinal shell component edges. 6. The fuselage segment according to claim 2, characterized in that several of the shell component rows of the plurality of shell component rows respectively form a closed ring. 7. The fuselage segment according to claim 2, characterized in that several shell component rows of the plurality of shell component rows are arranged behind one another in the longitudinal shell component direction, wherein two respective shell component rows that are arranged behind one another are connected at their ends that are formed by lateral shell component edges such that the several shell component rows altogether extend in a helical fashion in the circumferential direction and along the longitudinal fuselage segment axis. 8. The fuselage segment according to claim 2, characterized in that several shell component rows of the plurality of shell component rows are connected to one another end to end by welding. 9. The fuselage segment according to claim 2, characterized in that the connection of longitudinal shell component edges and/or lateral shell component edges of respectively different interconnected shell components is realized such that the respective interconnected shell components overlap one another with edge sections extending on the respective longitudinal shell component edges and/or lateral shell component edges, and in that the respectively overlapping edge sections are bonded to one another. 10. The fuselage segment according to claim 2, characterized in that at least one shell segment features at least one opening in the form of a window opening for installing a window glass and/or a passenger door opening for installing a passenger door and/or a cargo door opening for installing a cargo door, wherein the respective peripheral edge of the opening is situated within the region, in which the respective shell component extends in a planar fashion. 11. A method for manufacturing a fuselage segment with shell components that are mounted on a support structure and form a skin of the fuselage segment that extends in a longitudinal fuselage segment axis and is closed in a circumferential direction extending around the longitudinal fuselage segment axis, characterized in that a plurality of shell component rows is formed on the support structure by arranging and mounting shell components on the support structure in such a way that at least the direction of a tangent on first shell component edges, on which two respective shell components are connected to one another, and/or on second shell component edges, on which two respective shell components are connected to one another, extend at an acute angle relative to the longitudinal fuselage segment axis and, in particular, at an angle of 30° to 60° relative to the longitudinal fuselage segment axis. 12. The method for manufacturing a fuselage segment according to claim 11, characterized in that a plurality of shell component rows is formed on the support structure by arranging and mounting shell components on the support structure in such a way that the local direction of the center line of the respective shell component rows being formed extends at an angle of less than 90 degrees relative to the longitudinal fuselage segment axis. 13. The method for manufacturing a fuselage segment according to claim 11, characterized in that the shell components are arranged and mounted on the support structure in such a way that one respective shell component row is successively arranged behind another shell component row in the longitudinal fuselage segment axis.
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