Flexible assembly deviation analysis method for laminated structural member in consideration of interference connection

Abstract

The invention discloses a flexible assembly deviation analysis method for a laminated structural member in consideration of interference connection. The method is specifically implemented according to the following content: acquiring an initial stiffness matrix of a wallboard part; adopting a flexible tool for positioning and clamping the wallboard part according to a N-2-1 positioning principle; positioning and clamping positioning parts according to the position of the wallboard part, performing interference connection on the positioning parts and the wallboard part one by one, and after interference connection of one positioning part is completed once, calculating the springback values of all key feature points on the wallboard part after interference connection of the positioning part on the basis of an influence coefficient method, and calculating the springback deformation of the wallboard part on the matching surface of a next positioning part and the wallboard part until all the positioning parts are clamped; and recording the displacement of the concerned point of the final wallboard part so as to obtain the flexible assembly deviation of the laminated structural member. According to the invention, based on the consideration of the interference internal stress, the accuracy of assembly deviation analysis is improved.

Description

technical field [0001] The invention belongs to the technical field of flexible parts assembly, and relates to a method for analyzing the deviation of flexible assembly of laminated structural parts under consideration of interference connection. Background technique [0002] Laminated thin-walled structural parts made of fiber reinforced materials have the characteristics of high performance and light weight, and are widely used in aircraft skin parts. As the main connection method, interference fit introduces interference stress on the surface of the material during the connection process, which can improve the fatigue life of the joint. However, thin-walled composite parts have the characteristics of large size, low stiffness, anisotropy, etc. In the process, the shape error, positioning error, and installation error of the part itself will inevitably cause deformation, which will affect the assembly quality of subsequent aircraft components and final assembly. [0003] ...

AI Technical Summary

Problems solved by technology

Composite wall panel parts are connected and assembled through interference connection such as riveting and high-lock bolts. The hole wall at the joint inevitably introduces stress along the layer, and because the panel parts are thin-walled flexible parts, it will produce obvious The stiffening effect of the assembly makes the springback deformation process of the assembly complex, and the traditional influence coefficient method will produce relatively large deviations in the analysis results

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