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Transverse butt connection between two fuselage sections

A technology of horizontal connection and joint, applied in the direction of fuselage, fuselage bulkhead, fuselage frame, etc., can solve the problems of increasing storage cost and assembly cost

Inactive Publication Date: 2014-07-23
AIRBUS OPERATIONS GMBH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

In the case of solid additions, several additions with different geometries must be kept, thereby increasing storage and assembly costs

Method used

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  • Transverse butt connection between two fuselage sections
  • Transverse butt connection between two fuselage sections
  • Transverse butt connection between two fuselage sections

Examples

Experimental program
Comparison scheme
Effect test

Embodiment Construction

[0041] figure 1 A schematic diagram of a transverse joint connector designed according to the invention is shown.

[0042] The transverse joint connection body 1 is formed between a first and a second fuselage section 2 , 3 which are each surrounded by a skin 4 , 5 . The end regions 6 , 7 of the fuselage sections each have oppositely inclined skin wedge surfaces 8 , 9 . The two fuselage sections 2 , 3 are connected by means of annular transverse webs 10 . The web 10 has, in the region of the bottom surface 11 , two oppositely inclined web wedge surfaces 12 , 13 adjoining each other centrally. Wedges 14 , 15 are respectively inserted between the transverse web 10 and the end regions 6 , 7 of the fuselage sections. Tolerance compensation between the fuselage sections 2 , 3 takes place via the wedges 14 , 15 in the radial and / or axial direction. The angle of inclination of the wedges 14, 15, as well as of the transverse web wedge surfaces 12, 13 and the skin wedge surfaces 8,...

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PUM

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Abstract

The invention relates to a transverse joint connection (1, 24) between two fuselage sections (2, 3, 25, 26), in particular for producing a nacelle of an aircraft. The segment has a plurality of longitudinal beams (41, 42) arranged internally parallel to each other and evenly spaced apart on the skin (4, 5, 27, 28). In order to achieve universal tolerance compensation using standardized compensation methods within a predetermined tolerance zone between the two fuselage sections to be joined together, it is proposed according to the invention that the fuselage sections (2, 3, 25, 26) The two end regions (6, 7, 29, 30) have oppositely inclined skin wedges (8, 9) on the inside and are connected by a surrounding This is achieved by a transverse web (10, 31) which has two oppositely inclined transverse web wedges (12, 13) in the area of ​​the base (11), wherein in each transverse web wedge (12, Wedges (14, 15, 33, 34) can be inserted between 13) and the skin wedges (8, 9) for tolerance compensation between the fuselage sections (2, 3, 25, 26).

Description

technical field [0001] The invention relates to a transverse joint connecting body between two fuselage sections, in particular for making a nacelle of an aircraft, the fuselage section has a plurality of internally arranged parallel to each other at uniform intervals. Stringers on the skin. [0002] In addition, the invention relates to a method for producing such a transverse joint connection between two fuselage sections. Background technique [0003] In modern aircraft construction, so-called segmental construction types are widely used. In this case, otherwise prefabricated, in particular barrel-shaped, fuselage sections for producing a complete aircraft nacelle are arranged and connected to one another. The fuselage sections can be produced in a conventional aluminum construction type from a highly robust aluminum alloy material. In addition, fuselage sections are increasingly produced from fiber composite materials, such as carbon fiber-reinforced epoxy resins. A ...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64C1/12B64C1/06
CPCY10T29/49826Y02T50/433Y02T50/43B64C2001/0072B64C1/069B64C1/06B64C2211/00Y02T50/40
Inventor 福尔克尔·雷耶斯特凡·塔克斯蒂芬·米舍雷特
Owner AIRBUS OPERATIONS GMBH