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Method for manufacturing rudder assembly of aircraft by laser welding

A technology of aircraft rudder assembly and manufacturing method, applied in laser welding equipment, manufacturing tools, welding equipment and other directions, can solve the problems of unstable flight process of aircraft, cracking of resistance seam welding edge, etc., and achieve the effect of meeting product design requirements

Inactive Publication Date: 2013-01-09
SICHUAN FUTURE AEROSPACE IND LLC
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  • Summary
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  • Description
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  • Application Information

AI Technical Summary

Problems solved by technology

In the actual hypersonic flight of the rudder assembly processed in this way, due to the flight resistance, the edge part of the resistance seam welding will crack, causing the flight process of the aircraft to be unstable.
[0003] This shows that the above-mentioned existing aircraft rudder assembly still has deficiencies in the manufacturing method, and needs to be further improved urgently

Method used

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  • Method for manufacturing rudder assembly of aircraft by laser welding
  • Method for manufacturing rudder assembly of aircraft by laser welding
  • Method for manufacturing rudder assembly of aircraft by laser welding

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Embodiment Construction

[0028] see Figure 4 Shown, the manufacturing method of a kind of aircraft rudder assembly laser welding of preferred embodiment of the present invention, comprises the following steps:

[0029] A manufacturing method for laser welding of aircraft rudder components, comprising the following steps:

[0030] (1) Cutting, cutting the titanium alloy plate according to the size of the drawing;

[0031] (2) Hot press forming of the skin, thermoforming the 1.0-2.0mm thick plate to the requirements of the drawing, evenly brushing the protective alcohol graphite solution on the surface, lightly sanding with 600# fine sandpaper after air drying, and adjusting the upper and lower molds of the mold to keep the convex and concave The mold gap is 35-50mm, the mold temperature is raised to 550-750°C, pressurized to close the mold, keep warm for 5-30min, and take out the molded skin after cooling;

[0032] (3) Skeleton machining, the plate is machined and milled into a symmetrical profile a...

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Abstract

The invention relates to a method for machining a rudder assembly of an aircraft, in particular to a method for manufacturing a rudder assembly of an aircraft by laser welding. The method comprises the following steps of: (1) blanking; (2) machining and forming; (3) performing alkaline degreasing; (4) performing alkali washing; (5) performing acid washing; (6) washing; (7) drying; (8) performing laser welding; and (9) performing fine milling, so that the contour dimension meets the design requirement of the product. By the method, the problem of cracking of resistance roll welding edges of the rudder assembly is solved. The process for the rudder assembly by the laser welding plays an active role in the popularization and application of a laser welding rudder assembly in spacecrafts.

Description

technical field [0001] The invention relates to a processing method for an aircraft rudder assembly, in particular to a manufacturing method for laser welding of an aircraft rudder assembly. Background technique [0002] Aircraft rudder components are often realized by the structure of skeleton 1 and skin 2, such as figure 1 , figure 2 , image 3 As shown, the manufacturing method is to process the rudder frame 1 by machining, and form the skin 2 by hot pressing, and then weld the skin 2 to the frame 1 by resistance welding. The middle part of the skin is welded by resistance spot welding, and the edge of the skin is welded by resistance Seam welding. In the actual hypersonic flight of the rudder assembly processed in this way, due to the flight resistance, the edge part of the resistance seam welding will crack, causing the flight process of the aircraft to be unstable. [0003] It can be seen that the above-mentioned existing aircraft rudder assembly still has deficie...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B23P15/00B23K26/20B23K26/21
Inventor 王振强李亚丽胡鑫胡建国李波何东李凯祥李峰李鹏
Owner SICHUAN FUTURE AEROSPACE IND LLC