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Laser welding clamp for T-shaped structural component

A technology of laser welding fixtures and structural parts, which is applied in laser welding equipment, welding equipment, welding equipment, etc., can solve the problems of welding deformation that cannot be ignored, welding deformation, etc., achieve stable laser welding process, control deflection deformation, weld seam Uniform and continuous effect

Active Publication Date: 2015-01-07
SHANGHAI AIRCRAFT MFG +1
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0003] However, the T-shaped structural parts of the fuselage panel are thin-walled components, which are prone to welding deformation during the welding process. Although the heat input of laser welding is smaller than that of arc welding, given the large size of the thin-walled T-shaped structural parts, the thermal The input is greatly reflected on the overall wall plate, so that the welding deformation cannot be ignored

Method used

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  • Laser welding clamp for T-shaped structural component
  • Laser welding clamp for T-shaped structural component
  • Laser welding clamp for T-shaped structural component

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Embodiment Construction

[0031] The implementation and use of specific embodiments of the present invention are described in detail below. It should be understood, however, that the specific embodiments described are merely illustrative of specific ways to make and use the invention and do not limit the scope of the invention.

[0032] Such as figure 1 and figure 2 As shown, the laser welding jig for a large thin-walled T-shaped structural member according to the present invention includes a base plate 10 , a corner clamp 20 , and a bead 30 . Wherein, the base plate 10 is used to support the thin-walled skin 50 , and the bead 30 is used to press the thin-walled skin 50 so that the thin-walled skin 50 is close to the base plate 10 . combine Figure 4-Figure 5 As shown in , the angled pressing blocks 20 are respectively arranged at both ends of each stringer 60 and make the stringer 60 close to the thin-walled skin 50, and one end of the angled pressing block 20 is connected to the stringer 60, for ...

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Abstract

The invention discloses a laser welding clamp for a T-shaped structural component, and the T-shaped structural component comprises an envelope and a stringer, the laser welding clamp comprises a bottom plate for supporting the envelope; a pressing bar which is used to press the envelope such that the envelope is tightly close to the bottom plate; a corner-bending pressing block which is respectively arranged on both ends of each stringer, one end of the corner-bending pressing block is connected with the stringer while the other end thereof is connected with the bottom plate. The laser welding clamp can effectively control deflection deformation of the stringer and restrain generation and extension of solidification cracks at laser welding end points.

Description

technical field [0001] The invention belongs to the technical field of laser welding, and in particular relates to a laser welding jig for a large thin-walled T-shaped structural part, and is especially suitable for welding a fuselage skin-stringer structure. Background technique [0002] In 2001, laser welding technology was successfully applied to some fuselage panels of the small Airbus A318, and there are a large number of skin-stringer thin-walled T-shaped structures in these fuselage panels. The laser welding technology has successfully replaced the traditional riveting technology, resulting in a significant reduction in the weight of the fuselage, a significant reduction in production costs, and a significant increase in production efficiency, which also makes this technology effectively promoted in the processing and manufacturing of fuselage panels. [0003] However, the T-shaped structural parts of the fuselage panel are thin-walled components, which are prone to w...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B23K26/21B23K26/70B23K37/04
CPCB23K26/24B23K37/0435
Inventor 陈磊陈彦宾张澐龙刘红兵陶汪邓景煜
Owner SHANGHAI AIRCRAFT MFG
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