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Plate-made box-shaped member deep drawing limit determination method

A judging method and technology of box-shaped parts, applied in manufacturing tools, instruments, electrical digital data processing, etc., can solve problems such as cracking, uneven distribution of material stress, and uneven distribution of deformation

Active Publication Date: 2017-03-29
XI'AN AIRCRAFT INTERNATIONAL
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The complexity of the box-shaped part structure leads to uneven force distribution, uneven deformation distribution, and uneven deformation speed of the material during the deep-drawing forming process, resulting in various defects such as wrinkling, cracking, and springback on the surface of the part.

Method used

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  • Plate-made box-shaped member deep drawing limit determination method
  • Plate-made box-shaped member deep drawing limit determination method
  • Plate-made box-shaped member deep drawing limit determination method

Examples

Experimental program
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Effect test

Embodiment Construction

[0047] Such as Figure 1-8 As shown, a method for judging the drawing limit of a plate-made box-shaped piece includes the following steps:

[0048] Step 1: Determine the relative thickness of the box-shaped piece wool

[0049] Step 1-1: Use CAD software to extract the geometric information of the box-shaped part, and decompose the box-shaped part into web area 1, web fillet area 2, side wall area 3, flange area 6 and flange fillet In the five parts of zone 5, measure the thickness of the material as δ, and calculate the diameter of the wool as D 0

[0050] Step 1-2: Calculate the relative thickness C of the box-shaped piece wool based on the material thickness and wool diameter δ =δ / D 0 ;

[0051] Step 2: Determine the relative corner radius C of the box B

[0052] Step 2-1: Extract the intersection line L between web fillet area 2 and web area 1 WO , Measure the contour line L WO The distance between two opposite sides, the smaller the length is recorded as the bottom width B of t...

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Abstract

The invention provides a plate-made box-shaped member deep drawing molding limit determination method, which comprises: 1, determining the relative thickness C<delta> of a box-shaped member billet material, wherein C<delta> is delta / D0; 2, determining the relative corner radius C of the box-shaped member; 3, determining the maximum height of the box-shaped member; 4, determining the maximum corner-to-height ratio Cmax<R> of the box-shaped member; determining the maximum relative height Cmax<H> of the box-shaped member; 6, determining the deep drawing coefficient m of the box-shaped member; 7, determining the type of the box-shaped member; and 8, according to the two different types such as the high box-shaped member and the low box-shaped member, respectively determining the molding limits. According to the present invention, with the determination method, the part molding defect is predicted in advance, the production cost is reduced, the development progress us accelerated, and the promotion is easily achieved.

Description

Technical field [0001] The invention belongs to the technical field of aircraft manufacturing, and in particular relates to a method for determining the forming limit of an aircraft deep-drawn plate box-shaped part. Background technique [0002] Board-made box-shaped parts are widely used in aircraft parts and are classified as typical deep-drawn parts according to the processing method. Deep drawing refers to the pressing process of using a mold to force a metal slab into a three-dimensional hollow part. The three-dimensional hollow part is formed by the shrinkage and flow of the material on the outer edge of the blank. The complexity of the structure of the box-shaped part results in uneven distribution of stress, uneven distribution of deformation, and uneven deformation speed during the deep drawing process, resulting in various defects such as wrinkling, cracking, and springback on the surface of the part. [0003] Modern aircraft manufacturing requires sheet metal parts to h...

Claims

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Application Information

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IPC IPC(8): B21C51/00G06F17/50
CPCB21C51/00G06F30/17G06F30/20
Inventor 白颖韩艳彬程晓芳
Owner XI'AN AIRCRAFT INTERNATIONAL
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