Optimized distribution method of detection points on body wall board of large airplane

A technology of aircraft fuselage and layout method, applied in special data processing applications, instruments, electrical digital data processing, etc., can solve the problems of increasing assembly deformation estimation error and reducing the accuracy of panel pose evaluation.

Inactive Publication Date: 2015-04-08
ZHEJIANG UNIV +1
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AI Technical Summary

Problems solved by technology

Different detection point layouts contain different wall panel deformations. Unreasonable detection point layouts will reduce the accuracy of the pose evaluation of the wall panels and increase the assembly deformation estimation error.

Method used

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  • Optimized distribution method of detection points on body wall board of large airplane
  • Optimized distribution method of detection points on body wall board of large airplane
  • Optimized distribution method of detection points on body wall board of large airplane

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Embodiment Construction

[0043] Such as figure 1 As shown, the posture adjustment and positioning system for large aircraft fuselage panels is mainly composed of large aircraft fuselage panels 1 , numerical control positioners 2 and process joints 3 .

[0044] Such as figure 2 As shown, the large aircraft fuselage panel 1 is mainly composed of skin 4, stringer 5, bulkhead 6, corner piece 7 and other parts.

[0045] Such as image 3 As shown, the process joint 3 of the large aircraft fuselage panel 1 is mainly composed of a process ball joint 8 and a joint body 9 .

[0046] Such as Figure 4 As shown, the numerical control positioner 2 is mainly composed of an X-direction moving axis 10, a Y-direction moving axis 11, and a Z-direction moving axis 12, and each axis moves independently.

[0047] Such as Figure 5 As shown, the initial set of detection points to be selected is composed of multiple detection points 13 on the frame 6 .

[0048] The steps of the method for optimizing the layout of the...

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Abstract

The invention discloses an optimized distribution method of detection points on a body wall board of a large airplane. The method comprises the following steps: (1) building a wall board deformation process simulation finite element model based on movable traction of a numerical control locator without considering the dead weight of the wall board, and selecting a part of finite element node sets on a bulkhead for serving as initial detection point sets to be selected; (2) introducing each deviation source into the wall board deformation process simulation finite element model by taking the moving degrees of freedom of the numerical control locator in directions X, Y and Z to obtain corresponding wall board deformation modes; (3) building a wall board deformation mathematic model formed by overlapping wall board deformation modes, acquiring a Fisher information matrix comprising wall board deformation information from the wall board deformation mathematic model by using a least square method and an optimal moment estimation method, and selecting a required number of optimal detection point sets from the initial detection point sets to be selected by using an adaptive simulated annealing genetic algorithm with the determinant of a maximized Fisher information matrix as a criterion.

Description

technical field [0001] The invention relates to the technical field of aircraft assembly, in particular to a method for optimally arranging detection points on a fuselage panel of a large aircraft. 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. [0003] A large aircraft is usually composed of multiple fuselage sections, and the fuselage sections are spliced ​​by a plurality of wall panels 1 such as lower wall panels, side wall panels, and upper wall panels. The structure of the aircraft panel 1 is mostly a "semi-monocoque" structure, which is mainly composed of skin 4, stringer 5, bulkhead 6, corner piece 7 and other parts. Weaker, resulting in varying degrees of deformation during assembly. The deformation of the wall pan...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F19/00
Inventor 毕运波严伟苗柯映林沈立恒戚文刚彭婷婷葛小丽汪西
Owner ZHEJIANG UNIV
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