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A sheet metal forming method for aircraft skin parts with sag

A technology for aircraft skins and parts, which is applied in the field of sheet metal forming with sunken aircraft skin parts, can solve problems such as poor stretch forming mold sticking, and achieve the effects of improving satisfaction, saving mold costs, and avoiding workload

Active Publication Date: 2021-06-08
CHENGDU AIRCRAFT INDUSTRY GROUP
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] Aiming at the problem of poor die-fitting degree in stretch forming of aircraft skin parts with sags, a sheet metal forming method for aircraft skin parts with sags is proposed

Method used

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  • A sheet metal forming method for aircraft skin parts with sag
  • A sheet metal forming method for aircraft skin parts with sag
  • A sheet metal forming method for aircraft skin parts with sag

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0028] A sheet metal forming method with sunken aircraft skin parts is characterized in that it comprises the following steps:

[0029] a. According to the size of the part and the drawing die, the block material is cut;

[0030] b. Use the drawing die to stretch the parts through the skin stretching machine;

[0031] c. Roughly cut the shape of the part and drill the positioning pin hole;

[0032] d. Use the partial cover plate and the corresponding punch to suppress the sag on the hydraulic press,

[0033] e. Trim the shape of the part to the theoretical shape.

[0034] The detailed steps of the step a are as follows: the size of the lower block is based on the stretching direction of the skin along the stretching model surface plus a length of 600-700 mm.

[0035] The detailed steps of the step b are as follows: when stretching, part of the cover plate and the bushing for drilling need to be removed, and the parts are stretched and formed by using a drawing die.

[0036...

Embodiment 2

[0040] A sheet metal forming method with sunken aircraft skin parts is characterized in that it comprises the following steps:

[0041] a. According to the size of the part and the drawing die, the block material is cut;

[0042] b. Use the drawing die to stretch the parts through the skin stretching machine;

[0043] c. Roughly cut the shape of the part and drill the positioning pin hole;

[0044] d. Use the partial cover plate and the corresponding punch to suppress the sag on the hydraulic press,

[0045] e. Trim the shape of the part to the theoretical shape.

[0046] The detailed steps of the step a are as follows: the size of the lower block is based on the stretching direction of the skin along the stretching model surface plus a length of 600-700 mm.

[0047] The detailed steps of the step b are as follows: when stretching, part of the cover plate and the bushing for drilling need to be removed, and the parts are stretched and formed by using a drawing die.

[0048...

Embodiment 3

[0051] A sheet metal forming method with sunken aircraft skin parts is characterized in that it comprises the following steps:

[0052] a. According to the size of the part and the drawing die, the block material is cut;

[0053] b. Use the drawing die to stretch the parts through the skin stretching machine;

[0054] c. Roughly cut the shape of the part and drill the positioning pin hole;

[0055] d. Use the partial cover plate and the corresponding punch to suppress the sag on the hydraulic press,

[0056] e. Trim the shape of the part to the theoretical shape.

[0057] The detailed steps of the step a are as follows: the size of the lower block is based on the stretching direction of the skin along the stretching model surface plus a length of 600-700 mm.

[0058] The detailed steps of the step b are as follows: when stretching, part of the cover plate and the bushing for drilling need to be removed, and the parts are stretched and formed by using a drawing die.

[0059...

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Abstract

The invention belongs to the field of aviation parts processing, and in particular relates to a sheet metal forming method for aircraft skin parts with sags, which is characterized in that it comprises the following steps: a. cutting the block according to the size of the part and the drawing die; b. using the drawing die Stretch and form the parts through a skin stretching machine; c. Roughly cut the shape of the parts and drill the positioning pin holes; d. Use the partial cover plate and the corresponding punch to suppress the sag on the hydraulic press, e. Trim the parts From the shape to the theoretical shape, this invention uses the method of improving the mold structure to combine the two forming technologies through a set of tooling moulds, first stretching and then hydraulic pressure, which not only reduces the amount of manual correction through hydraulic forming subsidence, but also ensures product quality. Tooling costs are also saved.

Description

technical field [0001] The invention belongs to the field of aviation parts processing, and in particular relates to a sheet metal forming method for sunken aircraft skin parts. Background technique [0002] The aircraft skin is a force-bearing member that covers the outside of the fuselage frame. The direct function of the aircraft skin is to form a streamlined outer surface of the aircraft. At the same time, its interior needs to be riveted with structural parts such as stringers and flanges. The riveted area must fit the structural parts without excessive gaps. Therefore, the fit degree and surface quality of skin parts are very important to the whole aircraft. [0003] At present, the main sheet metal forming process of aircraft skin is: cutting material→stretching forming→manual rough cutting shape→manual correction→trimming the shape to the theoretical shape. This process is mainly formed by stretching by drawing die, but for skin parts with sag, such as figure 1 As...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B21D35/00
CPCB21D35/005
Inventor 赵梦娇董锦亮门向南钟立
Owner CHENGDU AIRCRAFT INDUSTRY GROUP
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