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Structural element for reinforcing a fuselage of an aircraft

A technology of structural elements and fuselage, applied in the field of structural elements, can solve the problems of increased weight of reinforced profiles

Inactive Publication Date: 2011-09-14
AIRBUS OPERATIONS GMBH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, this leads to a generally unreasonable increase in the weight of reinforcing profiles such as ribs and supports

Method used

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  • Structural element for reinforcing a fuselage of an aircraft
  • Structural element for reinforcing a fuselage of an aircraft
  • Structural element for reinforcing a fuselage of an aircraft

Examples

Experimental program
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Embodiment Construction

[0033] In the drawings, like reference numerals represent like constructional elements in each aspect.

[0034] figure 1 is a schematic cross-section of a structural element according to the invention. The structural element 1 includes in particular a reinforcement profile 2, which is in figure 1 The rib segments 3 are configured by way of example to reinforce a fuselage unit (not shown) of an aircraft. The rib segments 3 are manufactured from a suitable high strength aluminum alloy material and have a double T-shaped cross-sectional geometry. Alternatively, the rib segments 3 may have a U-shaped or L-shaped cross-sectional geometry. The rib segments 3 may be made from a one-piece solid aluminum alloy material, eg by milling, forging or stamping. According to the invention, the inner flange 4 of the rib segment 3 is bonded to the strip 5 over the entire surface. According to the invention, the strap 5 ideally almost prevents the propagation of cracks in the inner flange. ...

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PUM

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Abstract

The invention relates to a structural element (1,12,30) for reinforcing a fuselage of an aircraft, wherein the structural element comprises a reinforcement profile (2,13) which is made of a metallic material, particularly an aluminum alloy material or a titanium alloy material, as a single piece. According to the invention, the reinforcement profile is provided with a tab (5,14,24) at least in some areas. As a result of the tab, which is made of a fiber-reinforced layer material (7) or a fiber metal laminate and glued to a flange (20, 32) of the reinforcement profile at least in some areas, the structural element has a high damage tolerance and advantageous fatigue properties.; The fiber metal laminate or the layer material comprises a plurality of metal layers (8,34,43) and fiber-reinforced plastic layers (9,35,41) stacked in alternating fashion, said layers being glued to each other over the entire area. The reinforcement profile is joined to the tab through a joining layer (6,15,36). Said joining layer is constructed with preferably two prepreg layers (20,23,37,38) and a non-fiber-reinforced adhesive layer (21). The reinforcement profile is, for example, a curved rib segment (31) or a straight beam, both of which can be used particularly to brace a central and highly loaded fuselage section of a high wing aircraft. A crack (16) which forms in the area of an inner flange or an outer flange of the rib segment or of a reinforcement profile is bridged by the effect of the tab so that further propagation, if not completely prevented, is at least greatly slowed.

Description

technical field [0001] The invention contemplates a structural element for reinforcing an aircraft fuselage, said structural element comprising a one-piece reinforcing profile made of metallic material, in particular aluminum alloy material or titanium alloy material. Background technique [0002] A fuselage unit of an aircraft is usually made of a plurality of cylindrical fuselage sections arranged one behind the other and connected by transverse seams. Each fuselage section is reinforced by a plurality of annular ribs with fuselage cell skins laid over their outer surfaces. In order to further increase the stability of the fuselage section, a plurality of reinforcing profiles are arranged on the inner surface of the fuselage cell skin and extend in each case parallel to one another in the longitudinal direction of the fuselage section. The reinforcing profiles are also generally arranged distributed at uniform intervals from each other over the circumference of the fusela...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64C1/12B64C1/06
CPCB64C2001/0072Y02T50/43Y02T50/433B64C1/12B64C1/065Y10T428/24Y10T428/12389Y10T428/12347Y10T428/12569Y10T428/12486Y10T428/31678Y10T428/24612Y02T50/40
Inventor 尼古劳斯·奥赫洛夫托马斯·博伊姆勒德克·达韦霍特马泰斯·普洛克
Owner AIRBUS OPERATIONS GMBH
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