Forming method of saddle-shaped skin part

A technology of skin parts and saddle shape, which is applied in the application field of ribbed tooling, can solve the problems of rough grain, cracking, and inability to form blanks, and achieve the effects of reducing forming difficulty, increasing yield, and improving production efficiency

Inactive Publication Date: 2020-10-09
SHAANXI AIRCRAFT CORPORATION
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] When processing saddle-shaped double-curvature skin products, the material flows in the width direction after the upper mold tire is pressed down, which is perpendicular to the tension in the length direction. If the traditional forming process is used, because the blank is not constrained in this direction, the material will flow It flows quickly after being compressed, but it

Method used

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  • Forming method of saddle-shaped skin part
  • Forming method of saddle-shaped skin part
  • Forming method of saddle-shaped skin part

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Embodiment Construction

[0029] In order to further understand the invention content, characteristics and effects of the present invention, the following examples are given, and detailed descriptions are as follows in conjunction with the accompanying drawings:

[0030] see Figure 1-Figure 4 , tooling for forming double-curvature aircraft skin parts, including the upper workbench 1 of the drawing equipment, the upper drawing die 2, the part sheet 3, the lower workbench 4 of the drawing equipment, the clamping jaw 5 of the drawing equipment, the drawing Die drawbead 6.

[0031] In this embodiment, the drawing die is made of material QT700 casting, its strength and wear resistance are more than 30% higher than that of ordinary steel, and the surface of the drawing die is ground to ensure that the roughness is not less than 1.6, reducing the sheet metal The friction between the drawing die and the drawing bead of the drawing die increases the transmission of the drawing force to facilitate the flow of ...

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Abstract

The invention belongs to the field of forming and manufacturing of aerospace sheet metal parts, and relates to a ribbed tool and forming technology for forming of a double-curvature aircraft skin part. The tool is characterized by comprising a stretch-forming equipment upper workbench, an upper stretch-forming die, a plate material, a lower workbench, a clamping jaw, a stretch-forming die drawbeadand a lower stretch-forming die. The upper stretch-forming die is connected with the stretch-forming equipment upper workbench, the lower stretch-forming die is connected with the lower workbench, and convex rigs are additionally arranged on the stretch-forming dies. During skin stretch-forming, with the combination of pressure adjustment of the upper workbench and control over a friction lubricating mode, a blank maintains uniform bidirectional pulling force by changing the stress mode of the part through the drawbead, the uniformity and controllability of flowing of the part in the formingprocess are ensured, and rapid integral forming of the part with reverse double curvatures is realized.

Description

technical field [0001] The invention belongs to the forming and manufacturing industry of aviation skin stretched sheet metal parts, and relates to a forming method for saddle-shaped double-curvature aircraft skin parts and the application of ribbed tooling. Background technique [0002] Skin stretch forming is a typical sheet forming method in the field of aviation manufacturing. It is mainly used to produce large-scale skin parts that constitute the aerodynamic shape of the aircraft. The clamp clamps the plate, and then through the cladding stretching movement of the clamp or the vertical upward lifting movement of the drawing mold, the plate is gradually attached to the surface of the drawing mold and stretched and deformed to obtain the final shape. The characteristic of the drawing process is to add tangential tension while the plate is bending, so that the stress in the section of the plate tends to be uniform and reduce the bending moment caused by bending deformation...

Claims

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Application Information

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IPC IPC(8): B21D22/20B21D22/22B21D37/10B21D43/00B21D53/92
CPCB21D22/201B21D22/208B21D22/22B21D37/10B21D43/003B21D53/92
Inventor 关军苏颂涛王涵谢永鑫杨宗启黄雪峰
Owner SHAANXI AIRCRAFT CORPORATION
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