Digitizing correction method for aircraft panel assembling deformation based on triaxial numerical control locator

A technology of numerical control positioner and aircraft panel, which is applied in the field of digital correction and assembly deformation of aircraft panel, to reduce assembly stress and improve assembly quality

Active Publication Date: 2014-07-16
ZHEJIANG UNIV +1
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  • Abstract
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  • Application Information

AI Technical Summary

Problems solved by technology

[0005] Aiming at the deformation problem existing in the assembly of large aircraft panels at present, the present invention provides a digital correction method for assembly deformation of aircraft panels based on a three-axis numerical control positioner

Method used

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  • Digitizing correction method for aircraft panel assembling deformation based on triaxial numerical control locator
  • Digitizing correction method for aircraft panel assembling deformation based on triaxial numerical control locator
  • Digitizing correction method for aircraft panel assembling deformation based on triaxial numerical control locator

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Embodiment Construction

[0082] The present invention will be described in detail below in conjunction with the accompanying drawings and specific embodiments.

[0083] Such as figure 1 As shown, a large aircraft panel 1 is mainly composed of a skin 2, a stringer 3, a bulkhead 4, and a corner piece 5.

[0084] Such as figure 2 As shown in the figure, the process joint 6 of a large aircraft panel is mainly composed of a process ball joint 7 and a joint body 8 .

[0085] Such as image 3 As shown, the three-axis numerical control positioner 9 includes an X-direction movement axis 10, a Y-direction movement axis 11, and a Z-direction movement axis 12, each of which moves independently, and is manipulated and controlled by a control system computer 14. (wherein the coordinate system formed by the X-direction movement axis 10, the Y-direction movement axis 11, and the Z-direction movement axis 12 is as follows image 3 and Figure 4 shown. )

[0086] The process ball head 7 is spherically hinged at...

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Abstract

The invention discloses a digitizing correction method for aircraft panel assembling deformation based on a triaxial numerical control locator. The digitizing correction method comprises the steps that the relation between location error data of the motion parameter and detection point of the triaxial numerical control locator is built through a partial least squares regression inverting modeling method to obtain a digitizing correction model, digitizing correction of the large aircraft panel assembling deformation is achieved, assembling stress caused by assembling deformation on a large aircraft panel is effectively reduced, meanwhile, efficient and high-precision posture adjusting and butt joint of all panels in the fuselage section assembling process are guaranteed, and finally the assembling quality of large aircraft parts is improved. According to the digitizing correction method, the problem of correction and accurate locating of the large aircraft panel assembling deformation is successfully solved through the coordinate movement of the triaxial numerical control locator, the assembling stress caused by the assembling deformation to the large aircraft panel is effectively reduced, and the assembling quality of the large aircraft parts is improved.

Description

technical field [0001] The invention relates to the technical field of aircraft assembly, in particular to a method for digitally correcting assembly deformation of aircraft wall panels based on a three-axis numerical control positioner. Background technique [0002] As an extremely important part of the aircraft manufacturing process, aircraft assembly determines the final quality, manufacturing cost and delivery cycle of the aircraft to a large extent, and is the key and core technology in the entire aircraft manufacturing process. Large-scale aircraft are generally assembled by butt joints of multiple fuselage sections, and each fuselage section is assembled and spliced ​​by several wall panels. As one of the important components of modern large aircraft, the wall panel is not only an important part of the aerodynamic shape of the aircraft, but also the main load-bearing components of the fuselage and wings. Panel assembly is to position thin-walled parts such as skins, ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64F5/00B64F5/10
Inventor 毕运波严伟苗柯映林方伟卢鹄刘思仁薛雷汪西王平
Owner ZHEJIANG UNIV
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