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Stamping forming method for small-caliber and deep-cavity cap-shaped part

A stamping forming, deep cavity technology, applied in the field of sheet metal parts forming, hat bearing stamping, stamping and forming of aluminum alloy plate parts, can solve the complex structure of liquid-filled mold, the limited liquid-filled forming process, The wall thickness of parts is out of tolerance and other problems, so as to reduce the cost of trial and error, realize mechanized forming, and reduce the difficulty of processing.

Active Publication Date: 2021-03-26
XIAN AIRCRAFT IND GROUP
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0005] In order to solve the technical bottlenecks such as flange wrinkling, cap bottom cracking, part wall thickness out of tolerance, limited liquid-filled forming process, and complex liquid-filled mold structure during deep-drawing forming of small-caliber, deep-cavity hat-shaped supports, this project The purpose of the invention is to provide a stamping method for small diameter, deep cavity hat-shaped bearings

Method used

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  • Stamping forming method for small-caliber and deep-cavity cap-shaped part
  • Stamping forming method for small-caliber and deep-cavity cap-shaped part
  • Stamping forming method for small-caliber and deep-cavity cap-shaped part

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Embodiment Construction

[0039] Referring to the drawings, the aircraft parts provided by the examples are figure 1 As shown, the part is a small diameter, a deep cavity mount 1, mainly consisting of three major parts, including strip along the flange 2, the barrel side wall 3, and the cap type bottom 4. The diameter of the cap shaped bottom 4 and the strip of the flange 2 are close to 1: 3, and the cap-type support 1 once in the range of 0.38 ~ 0.42, the maximum problem with the prior art formation is the side wall 3 and the bottom 4 The phase is not formed in place, premature breakage.

[0040] Such as Figure 2-7 As shown, a small diameter, a stamped forming method of a deep cavity support, comprising the steps of:

[0041] Step 1: Construct a transition punch

[0042] The structure of the cap shaped support is a matrix, and a transition stamper 9 having a diameter is increased, and the depth of the cavity is lowered and the side wall has a constant inclination. Figure 2-5 Indicated.

[0043] Step 1-1:...

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Abstract

The invention provides a stamping forming method of a small-caliber and deep-cavity cap-shaped support. The stamping forming method comprises the steps of constructing a transition stamping part; determining a first-time stamping forming transition die structure; determining a second-time stamping forming die structure; performing first-time stamping forming; performing second-time stamping forming; and performing trimming and cutting. The method for determining an appearance structure of the transition stamping part is provided, calculation is easy, the machining difficulty of the small-caliber and deep-cavity part is lowered, mechanical forming of a limit blank is achieved, and the method has important practical value.

Description

Technical field [0001] The present invention relates to a sheet metal part shaped technique in the field of aircraft manufacturing, and is specifically used for a cap-type support punching forming method for small diameter, deep cavity and flange long-wide, is particularly suitable for material elongation less than 15. % Of the stamping of the aluminum alloy plate parts. Background technique [0002] Modern aircraft design concepts are lightweight, integrated, precision, high reliability, reduced a large number of complex welding structures and its welding and welding, and post-welding workload. [0003] In the domestic aircraft, the light aluminum alloy is used to achieve small size, the Draw is a small size than the overall design structure, which is small in size, such as with a straw hat, a hat diameter of 35-45mm, and the cap is long The proportion is close to 3: 2, the cap is 20-25mm, the upper diameter of the cap is close to the maximum length ratio of the maximum length o...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B21D22/02B21D37/10B21D37/18B21D43/00B21D53/92G06F30/17G06F30/15
CPCB21D22/02B21D37/10B21D37/18B21D43/003B21D53/92G06F30/17G06F30/15
Inventor 白颖钟李欣李世峰吴继文张立颜博
Owner XIAN AIRCRAFT IND GROUP
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