N-2-1 positioning based skin and stringer assembling deviation analyzing method of airplane

Abstract

The invention discloses an N-2-1 positioning based skin and stringer assembling deviation analyzing method of an airplane. The method comprises the following steps: positioning and clamping a skin based on the N-2-1 positioning principle; calculating the value of assembling clearances, at riveting points, of the skin and stringers; building a contact force model to solve the contact force; analyzing the influence of the contract force applied to the skin at a positioning and clamping point on a sensitivity matrix and a sub-assembly stiffness matrix; calculating the deformation of corresponding key feature points on the skin after the riveting of each stringer when a plurality of stringers are riveted on the skin; analyzing the influence of different stringer assembling sequences on the final assembling deformation; and evaluating different stringer assembling sequences to obtain the optimal assembling sequence. According to the method, the influence of the contact force and different stringer assembling sequences on the skin and stringer assembling deviation is analyzed in detail, so that the airplane wallboard assembling deviation can be accurately predicted, and as a result, the airplane assembling quality can be improved.

Description

technical field [0001] The invention belongs to the field of assembly deviation analysis of flexible parts of aircraft wall plates, and in particular relates to an analysis method for assembly deviation of aircraft skin and long truss based on N-2-1 positioning. Background technique [0002] In the assembly process of aircraft panel components, due to the influence of factors such as manufacturing errors and positioning errors of flexible parts such as skins and long trusses, and the positioning and installation errors of assembly tooling, there are inevitably some problems in the assembly process of flexible parts. degree of deformation. Assembly deformation seriously affects the assembly accuracy of aircraft panel components, which in turn affects the assembly quality of subsequent aircraft components and final assembly. [0003] Aircraft siding components are assemblies assembled from skins and trusses, bulkheads or ribs and other skeleton parts. The prediction of their ...

AI Technical Summary

Problems solved by technology

This method is based on the assumption of a rigid body, ignoring the characteristics of large size, small stiffness, and easy deformation of flexible parts, resulting in low efficiency and poor accuracy in the analysis of assembly deviations, and often requires repeated debugging during the assembly process

With the development of digital manufacturing technology, more and more aircraft manufacturing enterprises use flexible tooling based on the N-2-1 positioning principle to position and clamp skin or panel components. The modeling method of assembly deviation of aircraft panel components is still immature, and there is no mature analysis method for the contact force on the skin during the assembly process and the influence of different stringer assembly sequences on the final assembly deviation

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