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Laser Shock Shape Calibration Method for Welded Integral Wall Panel

A laser shock, integral wall panel technology, applied in the field of aviation manufacturing, can solve the problems of complex deformation and large deformation, and achieve the effects of large deformation, high work efficiency, and prevention of stringer deformation.

Active Publication Date: 2015-09-09
SHANGHAI AIRCRAFT MFG
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0005] One purpose of the present invention is to provide a shape correction method that can not only satisfy the precise shape correction of the deformation area but also realize the large curvature deformation in view of the complex deformation and large degree of deformation after laser welding of the welded integral wall plate

Method used

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  • Laser Shock Shape Calibration Method for Welded Integral Wall Panel
  • Laser Shock Shape Calibration Method for Welded Integral Wall Panel
  • Laser Shock Shape Calibration Method for Welded Integral Wall Panel

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Embodiment Construction

[0033] As required, specific embodiments of the invention are disclosed herein. It should be understood, however, that the embodiments disclosed herein are merely typical examples of the invention, which may be embodied in various forms. Therefore, specific details disclosed herein are not to be interpreted as limiting, but merely as a basis for the claims and as a representative basis for teaching one skilled in the art to variously employ the present invention in any appropriate manner in practice, This includes taking various features disclosed herein in combination with features that may not be expressly disclosed herein.

[0034] Figure 1 to Figure 4 The schematic diagrams before and after deformation of a double-curvature welded integral wall plate involved in the present invention are shown. from Figure 2 to Figure 4 It can be seen that both the skin 1 and the long stringer 2 welded on the skin 1 of the double-curvature welded integral panel 100 are deformed, where...

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Abstract

The invention relates to a laser shock shape-correcting method for welded integral panels. The laser shock shape-correcting method includes: S1) measuring deformation and residual stress; S2) determining a shape correcting amount and a shape correcting route by a computer; S3) determining strength of laser shock shape correcting by the computer; S4) performing laser shock shape correcting on the welded integral panel by laser shock equipment according to the strength and the shape correcting route determined by the computer; S5) performing shape correction detecting on the welded integral panel, if a film pasting interval is over a preset interval, sequentially repeating the steps S1, S2, S3 and S4 to enable the film pasting interval to approach to the preset interval, and stopping repeating until the film pasting interval is smaller than or equal to the preset interval. Compared with a conventional mechanical shape correcting method, the laser shock shape-correcting method has the advantages of high control accuracy and working efficiency, wide application range and the like, and meets standards of high requirement of aeronautical parts.

Description

technical field [0001] The invention relates to the technical field of aviation manufacturing, in particular to a method for laser impact correction and strengthening of the deformation of a welded integral wall plate. Background technique [0002] The siding structure of traditional aircraft mainly includes integrally machined siding and riveted siding. For integrally processed wall panels, the manufacturing method has low material utilization, very high manufacturing cost, and extremely low efficiency. Riveted siding will increase the overall weight of the aircraft, while the rigidity and strength are far less than integrally machined siding. [0003] After that, in the 1990s, Airbus took the lead in researching the laser welding technology of fuselage panels, which was successfully applied to the manufacture of aircraft fuselage panels of A318, A340 and A380. The welding technology replaces the riveting process, reducing the structural weight by 10% and reducing the cos...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B21D1/00
Inventor 刘红兵秦涛邓景煜陶汪王玉华陈彦宾李昊张澐龙
Owner SHANGHAI AIRCRAFT MFG
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