Parameterization numerical control machining method and system for aviation large thin-wall non-rigid part

Abstract

The invention provides a parameterization numerical control machining method and system for a large thin-wall non-rigid part in aviation. The parameterization numerical control machining method comprises the steps that 1, a workpiece is clamped; step 2, marking Mark points; step 3, planning a scanning path; step 4, point cloud scanning; step 5, deformation analysis; 6, adjusting a POGO column; step 7, carrying out secondary scanning; 8, based on the secondary point cloud and the three-dimensional design model, the positioning error of the large thin-wall part is obtained; and 9, on the basis of the positioning error obtained in the step 8, the machining code of the large thin-wall part is compensated. According to the method, the clamping and positioning error of the array type flexible supporting tool and the deformation error of the large aviation thin-wall non-rigid part can be effectively detected, a numerical control machine tool machining code is compensated and corrected on the basis, machining is conducted on the basis, and therefore the machining precision of the aviation thin-wall part is greatly improved, and the machining efficiency of the large aviation thin-wall non-rigid part is improved. And therefore, the quality stability of thin-wall parts in aerospace manufacturing is improved.

Description

technical field [0001] The invention relates to the technical field of numerical control machining of aerospace, in particular to a parametric numerical control machining method and system for large thin-walled non-rigid parts of aviation. Background technique [0002] Aviation large-scale thin-walled non-rigid parts such as integral skins and thin plates are widely used in the field of aviation manufacturing. Due to the characteristics of large size, small thickness, and easy deformation of such parts, the traditional clamping and positioning methods are difficult to apply. Therefore, at present, the method of array flexible support tooling is mostly used for clamping and positioning, so as to carry out subsequent processing. [0003] Patent document CN110110414A (application number: CN201910343950.7) discloses a thin-walled blade machining error compensation geometric modeling method, which is used to solve the technical problem of poor machining accuracy of existing erro...

AI Technical Summary

Problems solved by technology

[0005] 1) Positioning error: Due to the streamlined geometric shape of large thin-walled aviation parts and the special support principle of the array flexible support tooling, there is a lack of accurate positioning references during the clamping process

Thin-walled parts generally have problems such as low clamping accuracy and large positioning errors, which need to be adjusted by the master worker based on experience;

[0006] 2) Deformation error: Thin-walled parts will be partially deformed under the action of various factors such as their own gravity, clamping support force and internal stress

[0007] The existence of the above problems will inevitably affect the machining accuracy and seriously restrict the further improvement of the machining quality of large thin-walled aviation parts

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