带有翻边孔的复合材料C形件自动化制造工艺研究  

The Research on Automatic Manufacturing Process of C Section Composite Parts with Flanged Holes

作　　者：孙亚飞 赵科新 晏冬秀 谢汶轩 赵冲 SUN Yafei;ZHAO Kexin;YAN Dongxiu;XIE Wenxuan;ZHAO Chong(COMAC Shanghai Aircraft Manufacturing Co.,Ltd.,Shanghai 201324,China)

机构地区：[1]中国商飞上海飞机制造有限公司,上海201324

出　　处：《高科技纤维与应用》2023年第2期38-44,共7页Hi-Tech Fiber and Application

摘　　要：为满足内部维修、安装以及结构减重的需求,民用飞机复合材料肋零件通常会在肋腹板上进行开孔,并采用加筋或者局部增厚的方式进行补强。采用翻边孔结构设计在减少孔边裂纹风险的同时,可以减少加强件的使用,有利于提高结构效率。目前国内暂无复合材料翻边开孔结构零件的自动化制造经验,本论文针对此类零件的自动化制造工艺开展研究。通过探索不同剪口形式料层的可制造性,确定剪口数量及形状,通过分析翻边孔结构和C形结构一次热隔膜预成型的工艺过程,确定工装结构功能需求和设计形式,最终探索出含翻边孔C形结构复合材料零件的一次热隔膜预成型工艺方法。For civil aircraft composite rib parts,in order to satisfy the requirements of internal maintenance,installation and structural weight reduction,holes are usually opened on the rib wed,and stiffener or local thickening is used for reinforcement.The flanged hole structure can not only reduce the risk of hole edge cracks,but also reduce the use of reinforcements,which is conducive to improving structural efficiency.At present,there is no domestic experience on automatic manufacturing of this kind of part,so this paper focuses on this process study.By exploring the manufacturing of different shear forms,the number and shape of the notch have been determined.By analyzing the hot drape preforming process of the flanged hole structure and the C section structure at the same time,the functional requirements and design forms of the molding tooling have been determined.Finally,the one-time hot drape preforming process method for C section composite parts with flanged holes has been worked out.

关 键 词：翻边孔 C形结构 复合材料 热隔膜预成型 

分 类 号：TB332[一般工业技术—材料科学与工程]