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A Forming Method of Multi-extension Parts

A technology for parts and unfolding materials, applied in the field of forming parts of aircraft rocker arms with multiple extension, can solve the problems of complex forming process, low success rate, aperture deformation, etc., and achieve the effect of reducing scrap rate, reducing workload and improving quality

Active Publication Date: 2017-06-06
HARBIN
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The forming process of this type of parts is complex and highly operable
[0003] The rocker arm part is an atypical flanged cylindrical part, and wrinkles will appear after repeated forming, and heat treatment and manual calibration will easily lead to aperture deformation
Especially when the rocker arm is formed in the existing technology, it is divided into multiple continuous extensions, and then closed after multiple extensions are in place. Wrinkles and cracks are easily generated during the extension process, and the success rate is relatively low, which cannot meet the precision requirements of aircraft rocker products.

Method used

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  • A Forming Method of Multi-extension Parts
  • A Forming Method of Multi-extension Parts
  • A Forming Method of Multi-extension Parts

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Experimental program
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Embodiment Construction

[0029] Below in conjunction with accompanying drawing and embodiment the present invention will be further described:

[0030] The forming method of the multi-extension part of the present invention uses the drawing die to carry out multiple drawing and hole forming on the developed material, and then closes the drawn drawing hole for many times, and finally obtains the part meeting the size requirement of the product.

[0031] see figure 2 , which provides the implementation process of the forming method of the multiple extension parts of the present invention, the specific steps are as follows:

[0032] 1. Cutting

[0033] Cutting size 210x100xTH2.5 with shearing machine.

[0034] 2. Preparation of unfolded material

[0035] The experience obtained through many tests is expanded, and blanking is carried out with a blanking die.

[0036] 3. Make positioning holes

[0037] Make the Φ6.2 positioning hole with the experiential unfolding template.

[0038] 4. Stamping exte...

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Abstract

The invention belongs to the forming technology of rockers of aircraft, and particularly relates to a forming method for a repeatedly-extended part of a rocker of an aircraft. According to the forming method for the repeatedly-extended part, repeated extending and hole forming are performed on an unfolded material by utilizing an extending mould; and then repeated opening closing is performed on a formed extension hole, so that the part meeting the requirement of a product dimension is finally obtained. According to the forming method for the repeatedly-extended part, out-of-tolerance of the diameter of the hole is avoided; the working load of manual sizing is reduced; the quality is improved; and the rejection rate of parts is lowered.

Description

technical field [0001] The invention belongs to the forming technology of an aircraft rocker arm, and in particular relates to a forming method of a multiple extension part of an aircraft rocker arm. Background technique [0002] The rocker arm part is one of the most important parts of the aircraft control system. It is manufactured with high precision and is an atypical flange cylindrical part, such as figure 1 As shown, the size of the flange is different, the diameter of the cylinder is small, and the height is high. After multiple extensions and closing, trimming, and flanging, the part can be formed. The forming process of this type of parts is complex and highly operable. [0003] The rocker arm part is an atypical flange cylindrical part. Wrinkles will appear after multiple formings. Heat treatment and manual calibration will easily lead to aperture deformation. In particular, when the rocker arm is formed in the prior art, it is stretched several times in a row, a...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B21D35/00
Inventor 袁志强王安良
Owner HARBIN
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