飞机结构件轮廓特征加工自动分区算法

高鑫; 李仁政; 王斌利; 李卫东; 赵中刚

doi:10.7527/S1000-6893.2021.25346

航空学报 >

2021 , Vol. 42 >Issue 7: 625346 - 625346

DOI: https://doi.org/10.7527/S1000-6893.2021.25346

先进制造技术与装备专栏

飞机结构件轮廓特征加工自动分区算法

高鑫 ,
李仁政 ,
王斌利 ,
李卫东 ,
赵中刚

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航空工业成都飞机工业(集团)有限责任公司, 成都 610091

收稿日期: 2021-01-30

修回日期: 2021-02-25

网络出版日期: 2021-04-29

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Automatic partition algorithm for profile feature machining of aircraft structural parts

GAO Xin ,
LI Renzheng ,
WANG Binli ,
LI Weidong ,
ZHAO Zhonggang

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AVIC Chengdu Aircraft Industrial(Group) Co., Ltd., Chengdu 610091, China

Received date: 2021-01-30

Revised date: 2021-02-25

Online published: 2021-04-29

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摘要

作为飞机结构件重要组成部分，轮廓特征包含大量复杂曲面，且与工艺凸台等干涉物相连接，使得轮廓特征编程需综合考虑复杂曲面及干涉物信息，在自动编程模式下，轮廓特征编程仍严重依赖人工经验，其编程周期占结构件编程周期的40%以上，严重影响了结构件编程效率。针对该问题，提出了一种综合考虑复杂曲面及干涉物信息的轮廓特征加工自动分区方法，基于相邻轮廓面连接边属性及凸边约束原则对轮廓面进行初分区，依据干涉物信息构建虚拟边界，并基于虚拟边界对轮廓面初分区结果进行横向和纵向加工区域划分，通过对划分区域进行合并得到轮廓特征加工分区结果。根据提出的方法开发了飞机结构件轮廓特征加工自动分区系统，经过多项典型飞机结构件测试，该方法稳定可靠，可为轮廓特征加工程序编制提供支撑。

关键词： 飞机结构件; 轮廓特征; 虚拟边界; 加工区域; 自动分区

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高鑫 , 李仁政 , 王斌利 , 李卫东 , 赵中刚 . 飞机结构件轮廓特征加工自动分区算法[J]. 航空学报, 2021 , 42(7) : 625346 -625346 . DOI: 10.7527/S1000-6893.2021.25346

Abstract

The profile feature of aircraft structural parts is connected with aerodynamic shapes, which contains a large number of complex surfaces. The process pad is mostly used for clamping, which results in numerous factors to be considered in profile feature programming. In the automatic programming mode, programming of profile features still relies heavily on manual labor, and the programming time of profile feature accounts for more than 40% of the whole programming time of the aircraft structural part. To address this problem, an automatic algorithm for profile feature partition considering the complex surface and interference objects information is proposed in this paper. First of all, the profile features are initially partitioned based on convex edge constraints and properties of connection edges between adjacent profile surfaces. Then, the virtual boundary is constructed based on the information of interference objects. The horizontal and longitudinal machining regions of the initial partition results are divided based on the virtual boundary. Finally, the partition results for profile feature machining are obtained by combining the divided regions. An automatic partition system for profile features of aircraft structural parts is developed based on the proposed method. Testing of many structural parts shows that the proposed method is stable and reliable, and can provide support for profile feature programming.

Key words： aircraft structural parts; profile feature; virtual boundary; machining area division; automatic partition

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