Quick generation method of numerical control machining scheme of complex parts of airplane

Abstract

The invention discloses a quick generation method of a numerical control machining scheme of complex parts of an airplane, which mainly comprises the steps of: 1) obtaining machining technology information; 2) building the structural tree of the machining scheme; 3) generating the interaction display of the machining scheme; 4) quickly coding the machining scheme; 5) testing the effectiveness of the machining scheme; and 6) outputting the scheme. The method educates, normalizes and standardizes the machining scheme of the complex parts of the airplane, and improves the unitarity of the machining scheme, the reusability and the programming quickness, thereby shortening the programming period of numerical control machining scheme of the complex parts of the airplane, and improving the numerical control machining preparing efficiency and the machining quality.

Description

technical field [0001] The invention is a method for quickly generating a numerical control machining scheme of complex components of an aircraft, mainly used for the rapid generation of machining schemes in numerical control programming of integral structural parts of an aircraft, and is a professional and intelligent CAD / CAPP / CAM integrated system "quick numerical control machining of complex components of an aircraft" "Preparation system" provides a method for rapid generation of part processing schemes, and belongs to the technical field of aircraft digital numerical control programming. 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 integral thin-walled structural parts with superior performance (Fan Yuqing. Aerospace Manufacturing Engine...

AI Technical Summary

Problems solved by technology

However, due to the complex structure, high manufacturing precision requirements and difficult processing of the overall structural parts (Yu Fangfang, Du Baoorui, Ren Wenjie, ZhengGuolei, Chu Hongzhen. Slicing Recognition of Aircraft Integral Panel Generalized Pocket[J]. Chinese Journal of Aeronautics , 2008, (21): 585-592), the existing process preparation and NC programming methods have become the most important restrictive factors to further improve the quality and efficiency of aircraft overall structural parts manufacturing

For example, for a wall panel part, its CNC machining time is generally 2 to 3 days, but it takes 1 to 2 months to compile the CNC machining program of this type of part, and the programming time is much longer than the processing time

The root causes are mainly the following two aspects: one is the low level of knowledge, standardization and standardization of the processing plan, and the low efficiency of processing plan generation; the other is the low degree of automation of the programming process, which requires setting various processing options and processing through human-computer interaction. Processing parameters

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