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Forming method of aluminum alloy cabin section

A forming method and aluminum alloy technology, applied in metal processing equipment, laser welding equipment, arc welding equipment, etc., can solve the problems of increased production cost, low material utilization rate, increased production cycle, etc.

Active Publication Date: 2020-08-18
HUBEI SANJIANG AEROSPACE GRP HONGYANG ELECTROMECHANICAL
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  • Abstract
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  • Application Information

AI Technical Summary

Problems solved by technology

[0006] The invention provides a method for forming an aluminum alloy cabin section, which solves or partially solves the problem that in the prior art, the aluminum alloy cabin section is formed by friction stir welding of a forging ring and a sheet material, and it is impossible to realize a whole body with a super large diameter of 3.8m or above. The shell of the metal cabin is formed, the product processing allowance is high, the material utilization rate is low, the tooling structure is complicated, the production cost is increased, and the technical problems of the production cycle are increased

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  • Forming method of aluminum alloy cabin section
  • Forming method of aluminum alloy cabin section
  • Forming method of aluminum alloy cabin section

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Embodiment Construction

[0024] see Figure 1-5 , a method for forming an aluminum alloy cabin section provided by an embodiment of the present invention includes:

[0025] In step 1, the front frame 2 is formed by using arc additive manufacturing technology.

[0026] In step 2, the rear end frame 3 is formed by using arc additive manufacturing technology.

[0027] In step 3, the skin 4 is shaped according to the size of the front frame 2 and the size of the rear frame 3 .

[0028] Step 4, the front frame 2 , the rear frame 3 and the skin 4 are integrated by laser welding to obtain the aluminum alloy cabin section 1 .

[0029] Specific embodiments of the present application Because the arc additive manufacturing technology is used to shape the front frame 2, and the arc additive manufacturing technology is used to shape the rear frame 3, the front frame 2 and the rear frame 3 are formed by arc additive manufacturing. Technology, using the principle of layer-by-layer cladding, using the arc generate...

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Abstract

The invention discloses a forming method of an aluminum alloy cabin section, and belongs to the technical field of rapid forming. The forming method comprises the steps of forming a front end frame byadopting an electric arc additive manufacturing technology; forming a rear end frame by adopting the electric arc additive manufacturing technology; forming the skin according to the size of the front end frame and the size of the rear end frame; and integrating the front end frame, the rear end frame and the skin in a laser welding mode to obtain the aluminum alloy cabin section. According to the forming method of the aluminum alloy cabin section, forming of an integral metal cabin section shell with the ultra-large diameter of 3.8 m or above can be achieved, the product machining allowanceis reduced, the material utilization rate is increased, the tool structure is simple, the production cost is reduced, and the production cycle is shortened.

Description

technical field [0001] The invention relates to the technical field of rapid prototyping, in particular to an aluminum alloy compartment forming method. Background technique [0002] At this stage, the aluminum alloy cabin is usually formed by integral casting. However, due to the influence of the forming equipment and technical level, the aluminum alloy cabin with a large diameter is difficult to realize by the integral casting method. The riveting structure is adopted, but the efficiency is low. [0003] In the prior art, aluminum alloy cabins are formed by friction stir welding of forged rings and plates, with a diameter of up to 3.35 m, but it is difficult to form cabins with a diameter of 3.8 m or even a super large diameter of 4.5 m. [0004] Friction stir welding requires that the workpiece must have a rigid support to resist the upsetting force during welding, so special rigid support tooling is required, the structure is complex, the process preparation time is long...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B23K28/02B23K31/02B23K9/04B23K9/133B23K26/21
CPCB23K28/02B23K31/02B23K9/044B23K9/133B23K26/21
Inventor 吕天明庄玉蓉聂绪胜谢慧娟翟永卉
Owner HUBEI SANJIANG AEROSPACE GRP HONGYANG ELECTROMECHANICAL
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