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Aircraft fuselage structural element with variable section

A technology for aircraft fuselage and structural components, applied to aircraft parts, fuselage, fuselage frame, etc., can solve problems such as contour damage, and achieve the effect of reducing local wrinkles and reducing diffusion

Inactive Publication Date: 2014-02-12
AIRBUS OPERATIONS GMBH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0021] This is generally due to the fact that the substantially flat geometry of the flange in the direction of extension of the profile promotes a local distortion of the profile, thereby spreading the laminated part layers after impact and causing damage to the profile

Method used

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  • Aircraft fuselage structural element with variable section
  • Aircraft fuselage structural element with variable section
  • Aircraft fuselage structural element with variable section

Examples

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Embodiment Construction

[0051] In the remaining documents, a through cross section means a cross section transverse to the profile perpendicular to the local longitudinal direction in which the element extends.

[0052] Aircraft fuselage structural elements 1 in figure 1 , 2 and 3 partially show that the aircraft fuselage structural element is also referred to as a frame and has an overall shape that is partially elongated in the longitudinal direction.

[0053] Such as figure 1 As shown in , the profile extends along a curved surface enabling the structural element 1 to conform to the shape of the fuselage (not shown) to which it is fastened. The curved surface may have a fixed or variable radius.

[0054] In a preferred embodiment, said element 1 is made of continuous fiber reinforced composite material, for example produced by placing pre-impregnated fibers on a mould.

[0055] More specifically, for aerospace applications, the fibers are carbon fibers.

[0056] The structural element 1 compr...

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PUM

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Abstract

An aircraft fuselage structural element has the general form of an elongated profile and includes a web and at least one flange. The at least one flange has a curved cross-section tangent to the web. Use in a profile to increase the residual compressive strength after impact.

Description

technical field [0001] The invention relates to an aircraft fuselage structural frame element. Background technique [0002] Typically, an aircraft fuselage structure consists of a skin to which, among other things, elements are fastened, including structural elements known as rigid elements or frames. [0003] Typically, such structural elements are in the shape of a profile extending along a curved surface defined by a series of radii of curvature such that these structural elements conform to the specific curvature of the fuselage skin. [0004] The cross-section of said profile, which is substantially constant, is usually L, U or Z-shaped or other more or less complex shapes always comprising at least one plate and one or two flanges at one or both ends of the plate . [0005] When the structural material is made of metallic material (aluminum or titanium alloy), the frame is produced by using an extruded profile followed by deformation by plastic deformation such as s...

Claims

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Application Information

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IPC IPC(8): B64C1/06
CPCB64C1/06B64C1/061
Inventor 海伦妮·卡泽纳夫法布里斯·蒙泰耶扬·马尔基蓬特
Owner AIRBUS OPERATIONS GMBH