Transversal butt strap and method for connecting two especially wound cfk fuselage sections in order to create a fuselage cell
A technology of synthetic materials and spliced panels, which is applied in the direction of fuselage, aircraft parts, weight reduction, etc., can solve the problems of increasing manufacturing costs, time-consuming, dimensional deviation compensation, etc., to achieve large allowable deviations, avoid corrosion problems, and uniform tolerance compensation Effect
Inactive Publication Date: 2010-09-22
AIRBUS OPERATIONS GMBH
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Problems solved by technology
Occurring dimensional deviations cannot usually be compensated by conventional transverse splice panels
[0006] However due to tolerance issues encountered, a coiled CFRP-fuselage section cannot be directly joined to another coiled CFRP-fuselage section
Rather, a carbon fiber composite fuselage part consisting of at least two shell layers usually follows each wound carbon fiber composite fuselage part in order to be able to better compensate for radial tolerances, whereby Naturally increased manufacturing costs
Another possibility for tolerance compensation consists in using a compensation device in solid or liquid form, which is of course likewise disadvantageous from a manufacturing point of view because it is time-consuming
Method used
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[0030] Elements of the same structure in the figures each have the same reference numerals.
[0031] figure 1 A schematic cross-sectional view of a transverse splice plate constructed in accordance with the present invention is shown. The transverse splice plate 1 is connected to the inner side 3 of the skin 4 of the fuselage part 5 in the region of the end 6 of the fuselage part 5 by means of a plurality of riveting elements 2 . In the embodiment shown, the transverse splice plate 1 is formed by three overlapping plate parts 7 to 9 . The rivet connections 2 are preferably arranged in at least three columns extending over the entire circumference of the cylindrical fuselage 5 at evenly spaced intervals from each other. Instead of the rivet connection 2 shown, the transverse splice plate 1 can be connected to the skin 4 on the inside by any connecting technique, for example screwing, gluing, welding or any combination thereof.
[0032] figure 2 A view showing the transvers...
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The invention relates to a transversal butt strap (1, 19, 37) for producing a fuselage cell of an aircraft, by connecting a plurality of CFK fuselage sections (5, 26, 27, 43) produced especially by a winding method and respectively forming a transversal seam. The flexible transversal butt strap (1, 19, 37) is multi-layered, i.e. it comprises a plurality of strap segments (7-9, 20-23, 38-40) arranged one over the other, each strap segment (7-9, 20-23, 38-40) comprising a plurality of longitudinal slits (10, 11, 44, 45) that can respectively perform slight radial bending movements in order to generate a tolerance compensation in the radial direction between the fuselage sections (5, 26, 27, 43) to be joined together. A sliding movement is performed between the partial straps (17,18, 50, 51)of the strap segments (7-9, 20-23, 38-40) arranged one above the other, in the axial direction of the barrel-shaped fuselage sections (5, 26, 27, 43), and the ends (5, 26, 27, 43) of the fuselage sections (5, 26, 27,43) are bezelled (35, 36) on the inside thereof. The invention also relates to methods for creating a connection between two CFK fuselage sections (5, 26, 27, 43) preferably produced by a winding method, using a transversal butt strap (1, 19, 37) according to the invention.
Description
technical field [0001] The invention relates to a transverse splice panel for creating an aircraft cabin by joining a plurality of carbon fiber composite fuselage parts, in particular produced by the winding method, with the formation of transverse seams in each case. [0002] Furthermore, the present invention relates to a method for connecting fuselage parts, in particular carbon fiber composite material-fuselage parts produced by the winding method, also for the creation of a cabin. Background technique [0003] In modern aircraft construction, several fuselage parts are joined together by means of transverse splice plates to form a complete aircraft fuselage with the formation of circumferential transverse seams. The transverse splice plates are preferably riveted by means of riveting to the mutually engaging ends of the fuselage parts, respectively. On both sides of the transverse seam, two or three rivet arrays are arranged around the transverse splice plate and the ...
Claims
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IPC IPC(8): B64C1/00
CPCB64C2001/0072B64C1/069Y10T29/49346Y10T29/49622Y02T50/40
Inventor 安德烈亚斯·斯特凡
Owner AIRBUS OPERATIONS GMBH