Secondary correction method of aircraft skin numerical control machining program

Abstract

The invention provides a secondary correction method of an aircraft skin numerical control machining program. According to the skin shape and size, detection track planning is performed. A skin on-line detecting point position program is edited by CAM software for on-line detection of a machine tool. Point cloud data of a skin actual surface is obtained and is processed and fitted to form the actual surface. The secondary correction of a numerical control program is performed according to the actual surface, and the skin machining in an actual state is finished. The secondary correction method of the aircraft skin numerical control machining program can realize point position data fitting of a single curve or a hyperbolic skin and wall thickness program correction, and processes the mapping from a tool path with complex skin characteristics to the actual surface.

Description

technical field [0001] The invention relates to the technical field of machining, in particular to a method for secondary correction of an aircraft skin numerical control machining program. Background technique [0002] At present, the manufacturing process of aircraft skin generally adopts the chemical milling process, but with the development of green manufacturing technology, the mirror milling technology that can realize the green processing of aircraft skin has been introduced in China. In the process of using mirror milling technology, due to the influence of skin material rolling or stretching forming errors, clamping deformation, etc., the actual surface of the skin deviates from the theoretical surface. If the theoretical surface processing program is used, it will produce Larger wall thickness deviations lead to unqualified processed parts. [0003] In order to solve the problem of the deviation between the actual skin profile and the theoretical profile, a second...

AI Technical Summary

Problems solved by technology

In the process of using mirror milling technology, due to the influence of skin material rolling or stretching forming errors, clamping deformation, etc., the actual surface of the skin deviates from the theoretical surface. If the theoretical surface processing program is used, it will produce Large wall thickness deviation, resulting in unqualified processed parts

[0003] In order to solve the problem of the deviation between the actual skin profile and the theoretical profile, a secondary correction method for the NC machining program of aircraft skin is designed by using online detection and reverse forming technology, which can obtain the actual skin processing shape and modify the original The processing program is revised twice to finally solve the problem of wall thickness deviation caused by non-processing deformation such as raw material forming shape error and self-weight, and improve processing quality

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