飞机结构件内型转角一体加工刀轨生成方法

高鑫; 李迎光; 张臣; 刘长青; 郝小忠

doi:10.7527/S1000-6893.2013.0497

航空学报 >

2014 , Vol. 35 >Issue 9: 2660 - 2671

DOI: https://doi.org/10.7527/S1000-6893.2013.0497

材料工程与机械制造

飞机结构件内型转角一体加工刀轨生成方法

高鑫 ,
李迎光 ,
张臣 ,
刘长青 ,
郝小忠

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南京航空航天大学机电学院, 江苏南京 210016

高鑫男，硕士研究生。主要研究方向：CAM/CNC集成技术。Tel：025-84895906 E-mail：gaoxin@nuaa.edu.cn；李迎光男，博士，教授，博士生导师。主要研究方向：飞机数字化快速生产准备技术及软件开发，数字化设计制造，制造业信息化。Tel：025-84895835 E-mail：liyingguang@nuaa.edu.cn；张臣男，博士，副教授，硕士生导师。主要研究方向：数字化设计与制造技术，加工过程仿真与优化技术，加工状态监测与控制技术。Tel：025-84895906 E-mail：meeczhang@nuaa.edu.cn；刘长青男，博士研究生。主要研究方向：基于特征的加工监测检测一体化。Tel：025-84895906 E-mail：lchq0123@126.com；郝小忠男，博士研究生，高级实验师。主要研究方向：基于特征的智能装夹。Tel：025-84895906 E-mail：xhao@nuaa.edu.cn

收稿日期: 2013-11-06

修回日期: 2013-12-19

网络出版日期: 2013-12-30

基金资助

国家科技重大专项（2012ZX04010041）

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An Integrated Machining Tool Path Generation Method for Corner and Profile of Aircraft Structural Parts

GAO Xin ,
LI Yingguang ,
ZHANG Chen ,
LIU Changqing ,
HAO Xiaozhong

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College of Mechanical and Electrical Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China

Received date: 2013-11-06

Revised date: 2013-12-19

Online published: 2013-12-30

Supported by

National Science and Technology Major Project (2012ZX04010041)

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摘要

针对飞机结构件内型转角传统的分开加工易产生接刀痕以及转角处进给方向和刀具接触角急剧变化引起的切削力增大和刀具振动增强的问题，提出了飞机结构件内型转角一体加工工艺及其刀轨生成方法。该方法对内型和转角进行组合加工，首先计算满足接触角均匀变化的精加工所需余量和精加工刀轨，以及后续刀轨加工区域；其次在后续加工转角时通过采用最大和恒定接触角相结合的原则，循环分层加工转角，改善了加工状况。在刀轨连接处使用变螺旋曲线，保证了曲率的连续变化，减小了机床振动。切削实验表明：该刀轨改善了加工过程中的切削力和刀具振动，提高了工件表面的加工质量。

关键词： 飞机结构件; 内型; 转角; 加工; 切削力

本文引用格式

高鑫 , 李迎光 , 张臣 , 刘长青 , 郝小忠 . 飞机结构件内型转角一体加工刀轨生成方法[J]. 航空学报, 2014 , 35(9) : 2660 -2671 . DOI: 10.7527/S1000-6893.2013.0497

Abstract

In order to address the issues of cutting steps induced by the separated machining of corners and profiles of aircraft structural parts as well as the increase of the cutting force and vibration due to the sharp change of the feed angle at the corner and the contact cutting angle, an integrated machining process and its tool path generation method are proposed for machining the corners and profiles in aircraft structural parts. In the proposed method, profiles and corners in one pocket are machined in one machining operation. Firstly, the allowance is calculated for finish machining which can guarantee the uniform change of the cutting angle within limits. The machining area is also obtained for subsequent tool path. Then by using the combination principle of maximum and constant contact cutting angle in corner positions, the corner material is removed evenly by multiple passes. Therefore the cutting condition is improved. Clothoid curve segments are adopted so as to smoothen the transition of the tool path, ensure the continuous change of the curvature, as well as reduce the vibration of the machine tool. The cutting experiment results show that the proposed method can improve the conditions of the cutting force, reduce vibration during machining as well as improve the surface machining quality.

Key words： aircraft structural part; profile; corner; machining; cutting force

参考文献

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