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Online detecting method of numerical control machining middle state of plane structural member

A technology for aircraft structural parts and intermediate states, applied in computer control, program control, comprehensive factory control, etc., can solve problems such as lack of detection methods and intermediate state models, and achieve the effects of reducing processing costs, preventing influences, and ensuring processing quality.

Active Publication Date: 2013-01-09
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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Problems solved by technology

[0007] The purpose of the present invention is to invent an online detection method for the intermediate state of CNC machining of aircraft structural parts in view of the lack of detection methods and the construction of intermediate state models for the detection of intermediate states of large-scale aircraft structural parts CNC machining

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  • Online detecting method of numerical control machining middle state of plane structural member
  • Online detecting method of numerical control machining middle state of plane structural member
  • Online detecting method of numerical control machining middle state of plane structural member

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Embodiment Construction

[0041] The present invention will be further described below in conjunction with the accompanying drawings and embodiments.

[0042] Such as figure 1 , figure 2 shown.

[0043] A method for detecting an intermediate state of numerical control machining of aircraft structural parts, the method comprising the following steps:

[0044] Step 1. Select the surface required for intermediate processing state detection based on the final state of the CAD model of the part;

[0045] Step 2. Determine whether the selected surface is a three-axis processing surface or a five-axis processing surface. If it is a three-axis processing surface, offset the surface by a machining allowance value along the outer normal direction of the surface to form a theory of an intermediate processing state Surface; if it is a five-axis machining surface, use the surface formed by the sweeping surface formed by the tool to move along the tool track when machining the intermediate state of the surface a...

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Abstract

The invention discloses an online detecting method of a numerical control machining middle state of a plane structural member. First, a theoretical face of a middle machining state is established, for a three-axis face of finish machining, a face requiring detecting is selected according to the final state of a part computer-aided design (CAD) model, and a theoretical face of the middle machining state is formed by offsetting a working allowance value along the normal direction of the selected face. For a five-axis face of the finish machining, a face formed by scanning of an operation tool in the last step is used as the theoretical face of the middle machining state, a series of points are dispersed along a finish machining tool path and projected on the theoretical face of the middle state, detecting points of the middle state are formed, finally a detecting path is planned, and a numerical control (NC) program is formed to conduct online detecting. Theoretical thickness and theoretical distance are calculated according to the theoretical face of the middle machining state and form detecting result evaluation basis with a detecting point theoretical position. The online detecting method effectively solves the part quality problem caused by deformation of a large-scale part middle machining state and machining errors, and machining quality is guaranteed.

Description

technical field [0001] The invention relates to a numerical control machining method for aircraft structural parts, especially a detection method for the intermediate processing state, specifically for online detection of the intermediate state before numerical control machining of aircraft structural parts, belonging to CAD (Computer Aided Design) / CAM (Computer Aided Manufacturing) / CAI (Computer Aided Inspection) technical field. Background technique [0002] For large parts such as aircraft structural parts, due to their complex structure, large size and thin-walled parts, they are easily deformed during processing. At the same time, machining errors may be caused by tool wear and chatter of the processing system during processing. Deformation or machining errors in the machining process will affect the subsequent machining process or machining operations. In serious cases, the workpiece will be scrapped. Since aircraft structural parts are high-value and high-value-added ...

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G05B19/4097
CPCY02P90/02
Inventor 李迎光刘长青刘旭李海郝小忠王伟汤立民
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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