Method for producing part of an aircraft fuselage and tool for implementing said method

An aircraft fuselage, a part of the technology, applied in a part of the aircraft fuselage field, can solve problems such as uncontrollable internal stress

Active Publication Date: 2015-07-22
AIRBUS OPERATIONS (SAS)
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, in this case, for hollow cross-section frames, the internal stresses generated during assembly cannot be controlled

Method used

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  • Method for producing part of an aircraft fuselage and tool for implementing said method
  • Method for producing part of an aircraft fuselage and tool for implementing said method
  • Method for producing part of an aircraft fuselage and tool for implementing said method

Examples

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Embodiment Construction

[0055] Figure 2A , 2B and Figure 3-5 A panel of a portion of the aircraft fuselage, referenced 30, is shown.

[0056] In the description, once assembled, the panels 30 extend over half the section of the fuselage and are semi-cylindrical with a radius of curvature in a transverse plane. Of course, the present invention is not limited to this form. Thus, the shape of the panel 30 may not be a developable surface, having a double radius of curvature.

[0057] Panel 30 includes an inner surface 30I and an outer surface 30E, and is reinforced by stringers 32 connected to inner surface 30I. The panel 30 is defined by an upper edge 30H, a lower edge 30B and side edges 31, 31'. By way of example, each side edge is arranged in a transverse plane. The upper edge 30H corresponds to a part of the upper bus bar of the fuselage. The lower edge 30B corresponds to a part of the lower bus bar of the fuselage.

[0058] According to one embodiment, the panels 30 and the stringers 32 a...

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PUM

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Abstract

The subject matter disclosed herein relates to a method for assembling at least one panel and frames for producing part of an aircraft fuselage, the method including shaping the panel on support surfaces of a tool, wherein it includes holding each frame clamped against at least one sliding support surface arranged in a transverse plane, the sliding support surfaces of the various frames and the support surfaces being secured to the same tool and positioned relative to one another, and in putting in place permanent attachment elements for connecting the panel and the frames. The subject matter disclosed herein also proposes a tool for implementing the assembly method.

Description

technical field [0001] The invention relates to a method for manufacturing a part of an aircraft fuselage and a tool for carrying out the method. Background technique [0002] For the remainder of the application, the longitudinal axis corresponds to the axis extending from the front end to the rear end of the aircraft. A longitudinal direction is a direction parallel to the longitudinal axis. A longitudinal plane corresponds to a plane containing the longitudinal axis. A transverse plane corresponds to a plane perpendicular to the longitudinal axis. A radial direction is a direction perpendicular to the longitudinal axis. The inner surface or plane corresponds to the surface or plane towards the inside of the fuselage, and the outer surface or plane corresponds to the surface or plane towards the outside of the fuselage. [0003] As is known, the fuselage of an aircraft comprises structures mainly responsible for bearing forces and connecting skins (also called skins), ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64C1/06
CPCB29C67/0011B29C33/307B29C33/308B29L2031/3082B64F5/0009B64F5/10
Inventor 德尼·德马蒂亚
Owner AIRBUS OPERATIONS (SAS)
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