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Digitized correcting method for assembly deformation of aircraft panels based on six-shaft numerical control positioner

A numerical control positioner and aircraft panel technology, which is applied in the field of digital correction and aircraft panel assembly deformation, to achieve high-precision attitude adjustment and docking, improve assembly quality, and reduce assembly stress.

Active Publication Date: 2014-07-30
ZHEJIANG UNIV +1
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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 six-axis numerical control positioner

Method used

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  • Digitized correcting method for assembly deformation of aircraft panels based on six-shaft numerical control positioner
  • Digitized correcting method for assembly deformation of aircraft panels based on six-shaft numerical control positioner
  • Digitized correcting method for assembly deformation of aircraft panels based on six-shaft numerical control positioner

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Embodiment Construction

[0080] The present invention will be described in detail below in conjunction with the accompanying drawings and specific embodiments.

[0081] like 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.

[0082] like 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 .

[0083] like image 3 As shown, the six-axis numerical control positioner 9 includes an X-direction movement axis 10, a Y-direction movement axis 11, a Z-direction movement axis 12, an X-direction rotation axis 13, a Y-direction rotation axis 14, and a Z-direction rotation axis 15, and each axis moves independently , and the manipulation control is realized by the control system computer 17. Among them, 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 f...

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Abstract

The invention discloses a digitized correcting method for the assembly deformation of aircraft panels based on a six-shaft numerical control positioner. In the digitized correcting method, the relation between the motion parameter of the six-shaft numerical control positioner and the position error data of a detection point is built by a partial least squares regression inversion modeling method to obtain a digitized correcting model, so that the digitized correction of the assembly deformation of the panels of the large aircraft is realized, the assembly stress generated due to the assembly deformation of the large aircraft panels is effectively reduced, at the same time, the attitude adjustment and the butt joint with high effects and high precision for each panel during the assembly of the fuselage are ensured, and the assembly quality of large parts of the aircraft are finally improved. Through the coordinate movement of the six-shaft numerical control positioner, the digitized correcting method has the advantages that the problems of the assembly deformation correction and the accurate positioning of the panels of the large aircraft are successfully solved, the assembly stress generated by the assembly deformation of the large aircraft panels is effectively reduced, and the assembly quality of the large parts of the aircraft are 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 six-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, lo...

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屠晓伟姜丽萍沈立恒朱宇邢宏文周庆慧
Owner ZHEJIANG UNIV
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