Digital Correction Method of Aircraft Panel Assembly Deformation Based on Six-Axis NC Positioner
A technology of numerical control positioner and aircraft wall panel, which is applied in the direction of aircraft assembly, aircraft parts, ground installations, etc., to achieve the effects of reducing assembly stress, improving assembly quality, high-precision attitude adjustment and docking
Active Publication Date: 2015-08-26
ZHEJIANG UNIV +1
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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
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[0080] The present invention will be described in detail below in conjunction with the accompanying drawings and specific embodiments.
[0081] 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.
[0082] 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 .
[0083] Such as 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 1...
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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...
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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