Deformation calculation and auxiliary control method for main positioning frame for vertical assembly of fuselage

Abstract

The invention discloses a deformation calculation and auxiliary control method for a main positioning frame for vertical assembly of a fuselage, and belongs to the technical field of aircraft assembly. The implementation process comprises the following steps: determining position areas of auxiliary holes and auxiliary supporting points; establishing a polar coordinate system, determining auxiliary hole combination modes, and calculating the maximum deformation of the frame under different auxiliary hole combination modes; determining the combination modes of the process holes and the auxiliary supporting points, and calculating the maximum deformation of the frame in different combination modes; arranging an auxiliary supporting device; and selecting an optimal supporting mode. According to the method, the problem in assembling and positioning the main positioning frame in the vertical assembly process of the fuselage section can be solved, the assembly precision of the main positioning frame is guaranteed, positioning deformation if the main positioning frame in the assembly process is controlled in the structural design stage, rework adjustment in the assembly process is reduced, and the method is convenient to implement, wide in applicability and low in cost.

Description

technical field [0001] The invention relates to the field of aircraft assembly, in particular to a deformation calculation and auxiliary control method of a main positioning frame for vertical assembly of a fuselage. Background technique [0002] The vertical assembly of the middle fuselage section is as follows: figure 1 As shown, the main positioning frame is supported and positioned by the locator 2 on the tooling frame 1; and the beam 5 and the bottom plate 3 are assembled according to the direct assembly method with the main positioning frame as the positioning reference. The positioning between the locator and the main positioning frame mainly adopts the positioning of the hole pin, that is, the positioning pin is connected with the intersection hole and the process hole to limit the translation and rotation of the main positioning frame. [0003] When the main positioning frame is assembled and positioned, it will be deformed by its own gravity, and the deformation o...

AI Technical Summary

Problems solved by technology

[0008] The purpose of the present invention is to solve the problem that the calculation and analysis method of the deformation of the main positioning frame is insufficient during the vertical assembly process of the middle fuselage section, and the position of the process hole and the position of the auxiliary support point are all based on experience, which leads to assembly deformation during the assembly process. A deformation calculation and auxiliary control method of the main positioning frame of the fuselage vertical assembly. In the design stage of the middle fuselage section, the purpose of controlling the deformation of the main positioning frame is achieved by designing the position and quantity of the support points.

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