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Method of manufacturing elongate component

A technology for long parts and components, applied in program control, general control system, control/regulation system, etc., can solve the problems of time-consuming computing resources, high cost, etc.

Inactive Publication Date: 2013-03-06
AIRBUS OPERATIONS GMBH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

This would be extremely time consuming and costly for computational resources

Method used

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  • Method of manufacturing elongate component
  • Method of manufacturing elongate component
  • Method of manufacturing elongate component

Examples

Experimental program
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Embodiment Construction

[0034] refer to Figure 1a , shows an elongated aircraft wing stringer 10 having an upper surface 12 and a lower surface 14 . Such as Figure 1b As shown in , the example stringer is an I-beam having a top flange 24 and a bottom flange 26 .

[0035] The longitudinal beam 10 is supported at its lower surface 14 on two space supports 16 , 18 which are supported on the ground 20 . The punch 22 can be moved in the vertical direction in order to deform the stringer 10 between the two supports 16 , 18 . Such punching equipment is known and will not be described in detail here.

[0036] To deform the stringer to the desired profile of the aircraft wing, the punch 22 is advanced downwards with a force F by a punching offset d 冲压 . D. 冲压 is defined as the advance of the punch 22 from the initial position in contact with the top surface 12 of the stringer 10 to Figure 1c The amount of position.

[0037] Such as Figure 1c As shown in , the stringer 10 is deformed elastically an...

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PUM

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Abstract

A method of manufacturing an elongate element (10) using a punching operation assumes a polynomial relationship between punch depth (d punch ) and neutral axis, with the constants being a polynomial function of plastic deformation of the beam. Using finite element analyses, a relationship between the required plastic deformation, the second moment of area of the element and the neutral axis of the element can be derived.

Description

technical field [0001] The invention relates to a method of manufacturing an elongated part. More specifically, the present invention relates to a method of manufacturing elongated aircraft components, such as aircraft wing stringers, by causing plastic deformation by differential contact three-point bending operations. Background technique [0002] Components such as aircraft stringers need to be shaped into the aerodynamic profile of the wing. To achieve this, the stringers are plastically deformed by differential contact three-point bending. By "differential contact three-point bending" we mean a process by which a stringer is supported on a first side in two spaced positions. Stamping is applied therebetween from a second, opposite side to induce a bending moment, thereby causing localized plastic deformation. As the stringer deforms as the stamping progresses, the contact area with the punch and bracket may change. This is not a classic three-point bending load situ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B21D7/06
CPCB21D7/00G05B2219/36203G05B19/188G05B2219/49364B21D5/00B21D5/0281B21D7/12Y10T29/49
Inventor 沈伟铭O·阿德托罗文丕华
Owner AIRBUS OPERATIONS GMBH