Tool path generation method for residual area of complex corners in cavity of aircraft structural parts
A technology for aircraft structural parts and residual area, applied in the direction of electrical program control, digital control, etc., can solve problems such as dynamic load changes, and achieve the effects of small changes in cutting force, shortening CNC machining preparation time, and reducing tool wear.
Active Publication Date: 2017-01-11
SHENYANG AIRCRAFT CORP
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Problems solved by technology
[0003] In order to solve the above-mentioned existing technical problems, the present invention provides a method for generating toolpaths in the residual area of complex corners in the cavity of aircraft structural parts. Problems such as dynamic changes in the load during the cutting process to improve the quality of wall panel processing
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[0017] The invention is based on the CAD / CAM system platform, and realizes a method for calculating the angle of cavity of the aircraft wall panel and the tool track of the residual area of the narrow neck.
[0018] The embodiments of the present invention will be described in detail below in conjunction with the accompanying drawings. This embodiment is implemented on the premise of the technical solution of the invention, and detailed implementation methods and specific implementation processes are provided, but the protection scope of the present invention is not limited to The following implementation examples.
[0019] The detailed steps that the tool path calculation that the present invention proposes implements are as follows:
[0020] Step 1): Residual area acquisition. The main contents of residual area acquisition include: calculation of the cavity processing area; calculation of the machinable area of the previous tool; difference between the cavity processing...
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The invention provides an aircraft structural component cavity complex corner residual region tool path generation method. The method includes the first step of machining region acquisition, the second step of narrow neck partitioning, the third step of critical tool path calculation, and the fourth step of tool path ring calculation, wherein in the first step, by calculating the machining region of a cavity and the machinable region of the last tool, the difference between the machining region of the cavity and the machinable region of the last tool is solved to obtain the residual region to be machined; in the second step, the concave vertex and the concave edge of a narrow neck region are calculated, and the bottleneck line of the narrow neck region is determined through the concave vertex and the concave edge to serve as a parting line so as to partition the narrow neck region, so that the narrow neck region is converted into a plurality of corner regions; in the third step, the critical tool path calculation comprises hard critical tool path calculation, soft critical tool path calculation and virtual critical tool path calculation; in the fourth step, the soft critical tool path and the hard critical tool path are connected through circular arc transition, a return linear tool path is added, a first tool path ring is obtained through clipping, the cutting part of the tool path ring is biased according to the radial cutting-in depth to obtain a bias line link intersecting with the critical tool path, the bias line link and the critical tool path are connected through circular arc transition, the generation process of the first tool path ring is repeated till the bias line link does not have any point of intersection with either the hard critical tool path or the virtual critical tool path, and the final spiral ring tool path is generated.
Description
technical field [0001] The invention relates to a method for generating a tool track in a complex corner residual area of a cavity of an aircraft structural part, which is used for generating a tool track in numerical control programming of a corner area after rough machining of a complex structural part of an aircraft, and belongs to the technical field of aircraft digital manufacturing. Applying this method is suitable for tool path generation in any corner area after rough machining. It can calculate the tool path with uniform cutting thickness and continuously changing cutting force direction, improve the quality of aircraft wall panel cavity finishing, and reduce tool wear at the same time. Background technique [0002] The rapid development and wide application of computer, programming, high-speed cutting and other numerical control related technologies have promoted the development of aircraft structural parts manufacturing technology. Modern aircraft generally adopt...
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IPC IPC(8): G05B19/19
Inventor 杜宝瑞陈树林周敏郑国磊初宏震郑祖杰
Owner SHENYANG AIRCRAFT CORP