Large structural component self-adaptation machining method integrating machining, monitoring, detecting and clamping

Abstract

The invention discloses a large structural component self-adaptation machining method integrating machining, monitoring, detecting and clamping. The large structural component self-adaptation machining method is characterized in that a self-adaptation clamping device is used, self-adaptation adjusting clamping can be achieved in the machining process according to deformation of a workpiece, residual stress is released in the machining process, a displacement sensor and the clamping device are integrated, the deformation of the workpiece is monitored in real time through the displacement sensor, and feature machining sequence and tool path strategy adjustment are carried out according to the actual deformation condition; if the deformation is within the allowed range, the machining sequence is adjusted, and deformation of machining at the next step is reduced; if the deformation reaches an alarm value, on-machine testing is triggered, the tool path strategy is adjusted according to detected data, and the further-machined workpiece quality is ensured. According to the large structural component self-adaptation machining method, the deformation prediction problem based on residual stress and other uncertain factors is converted into the problem based on online monitoring, on-machine testing and other certain factors to be solved, and the final machined quality of the workpiece can be ensured fundamentally.

Description

technical field [0001] The invention relates to an adaptive processing method for large structural parts. On the basis of an adaptive clamping device, real-time monitoring of deformation, adjustment of processing sequence of monitoring trigger features and on-machine detection belong to the technical field of CAM / CNC, specifically a An adaptive processing method for large structural parts integrating processing-monitoring-detection-clamping. Background technique [0002] With the development of aircraft manufacturing and numerical control technology, integral structural parts are widely used in the aerospace field because of their light weight, high structural efficiency, and good reliability. However, due to the large-scale and thin-walled aerospace structural parts, the parts are affected by various factors during the processing process, and deformations such as bending, warping or combination of bending and torsion often occur after processing. The clamping force is the o...

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Problems solved by technology

[0006] The purpose of the present invention is to deal with the fact that the existing large-scale structural parts of aircraft are easy to deform during the processing process, and the deformation is difficult to control, resulting in size errors, shape errors and position errors, resulting in possible overcut or undercut in further processing, and severe cases. In order to deal with the scrapping of parts and

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