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Method of manufacturing an aircraft structure and structure obtained therefrom

A technology of aircraft and assembly method, which is applied in the direction of aircraft parts, fuselage, fuselage frame, etc., and can solve problems such as not very suitable and complicated assembly

Inactive Publication Date: 2016-06-15
AIRBUS OPERATIONS GMBH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

These components complicate assembly
According to another drawback, as mentioned above, the skin is shaped on a special tool, so its shape does not quite fit the shape of the frame, or wedges are inserted between the support and the skin

Method used

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  • Method of manufacturing an aircraft structure and structure obtained therefrom
  • Method of manufacturing an aircraft structure and structure obtained therefrom
  • Method of manufacturing an aircraft structure and structure obtained therefrom

Examples

Experimental program
Comparison scheme
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Embodiment Construction

[0034] exist image 3 , 5 In and 6, shown is a portion of an aircraft fuselage comprising a skin 28 reinforced in two directions with a first set of stiffeners and a second set of stiffeners, said first set of stiffeners being referred to as along the aircraft The reinforcing ribs 30 arranged in the longitudinal direction of the second group of reinforcements are called frames 32 arranged in a plane perpendicular to the longitudinal direction and ensuring the recovery of the track force.

[0035] Ribs 30 are provided on the inner surface of skin 28 by any suitable means.

[0036] As known, the skin 28 is in the form of a juxtaposition of panels or of a plurality of entire lengths of metal panels attached to the structure by means of rivets or by any suitable means. According to a variant, these panels may be of composite material.

[0037] Since the skin 28 and the ribs 30 are well known to those skilled in the art, they will not be described again.

[0038] According to t...

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PUM

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Abstract

The invention is an aircraft structure comprising a skin (28) reinforced in two directions with a first set of stiffeners and a second set of stiffeners, said first set of stiffeners being arranged in the longitudinal direction of the aircraft ribs (30), said second set of reinforcements is called a frame (32) arranged in a plane perpendicular to the longitudinal direction and ensuring recovery of track forces, characterized in that at least one frame (32) is composed of a closed A hollow section defined by a profile manufactured as a given section in one piece, a part of which is in contact with the skin.

Description

technical field [0001] The invention relates to a method of manufacturing an aircraft structure and to the structure obtained by said method. Background technique [0002] As is known, an aircraft fuselage comprises a structure mainly for ensuring force recovery, on which there is an outer skin, hereinafter referred to as the aerodynamic skin, which imparts its aerodynamic properties to the aircraft. Thus, the structure includes girders, stiffeners, stiffeners, etc. combined with each other. These elements may be metal and / or composite. [0003] Aerodynamic shells are known in the form of side-by-side plates or whole lengths of metal plates joined to the structure by means of rivets or by any suitable means. According to a variant, these panels may be of composite material. [0004] exist figure 1 A part of an aircraft fuselage is shown in , which includes a skin 12, ribs 14 on the inner wall of the skin and arranged longitudinally of the aircraft, and frames on which th...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64C1/06
CPCB64C1/068B64C1/12Y10T29/49826
Inventor 克里斯托夫·米亚勒埃莱娜·博内路易斯·佩尔蒂埃
Owner AIRBUS OPERATIONS GMBH