Airframe butt joint attitude-adjusting method meeting stringer reference alignment and straightness requirements

Abstract

An airframe butt joint attitude-adjusting method meeting stringer reference alignment and straightness requirements includes the steps: measuring end face reference points and linear guide rail reference points of a fixed airframe section and an attitude-adjusting airframe section and coordinates of the position of an attitude-adjusting system three-dimensional positioner connector connected with the attitude-adjusting airframe section by a laser tracker; building airframe end face reference point matching and straightness matching target functions, and accordingly building a mathematic model for airframe butt joint attitude-adjusting calculation; performing iterative calculation for the airframe butt attitude-adjusting model by a Gauss-Newton method to obtain coordinates of optimal butt joint positions of the attitude-adjusting airframe section and the fixed airframe section and obtain a transformational matrix from an initial position to a target position; calculating the coordinates of the target position of an attitude-adjusting system three-dimensional positioner connector connected with the attitude-adjusting airframe section according to the obtained transformational matrix, and butting the attitude-adjusting airframe section and the fixed airframe section by controlling movement of the attitude-adjusting system three-dimensional positioner from the initial position to the target position.

Description

technical field [0001] The invention belongs to the technical field of aircraft assembly, and relates to an attitude adjustment method for butt jointing of aircraft fuselages considering long girder reference alignment and straightness requirements. Background technique [0002] The docking assembly of large parts such as the fuselage of a large aircraft is a complicated process, and the alignment of the long-distance position on the end surface of the aircraft fuselage realizes the docking of the aircraft fuselage. During the docking process of the aircraft fuselage, not only the position matching of the reference point of the end surface of the fuselage needs to be considered, but also the overall straightness of the aircraft fuselage must be considered. The docking assembly of large parts such as the traditional aircraft fuselage mainly uses a large fixed docking platform, relying on the method of assembly frame and process compensation to coordinate the docking parts, an...

AI Technical Summary

Problems solved by technology

[0004] In order to overcome the problem of insufficient consideration of the matching information of the two docked fuselages brought about by controlling the attitude adjustment system only according to the target pose parameters provided when designing the aircraft when docking and assembling the existing aircraft fuselage and other large parts , to provide an aircraft fuselage docking attitude adjustment method that considers the long truss datum alignment and straightness requirements, and establishes the two-section docked fuselage end face datum point matching and fuselage rail straightness matching objective functions based on the least squares method, referring to the manual docking test The matching idea uses the Gauss-Newton method to iteratively calculate the aircraft fuselage docking attitude adjustment model, and obtains the target attitude parameters of the aircraft attitude adjustment fuselage section, which provides a pose basis for the motion control of the attitude adjustment system

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