用于整体化结构成型的复合材料工装设计和制造技术研究  

Research on Design and Manufacturing Technology of Composite Material Tools for Integrated Structural Forming

作　　者：付景丽 李璐璐 蔡骏文 FU Jingli;LI Lulu;CAI Junwen(AVIC GA Hua.nan Aircraft Industry Co., Ltd., Zhuhai 519040,China)

机构地区：[1]中航通飞华南飞机工业有限公司

出　　处：《航空制造技术》2019年第17期46-49,57,共5页Aeronautical Manufacturing Technology

摘　　要：介绍了轻型公务机中机身增压仓的制造方法。中机身是一个半封闭舱体,考虑到成型后零件的可脱模型,工装不能制作为一个整体,同时考虑加工和成型简便性,采用上下两部分来制造,解决零件铺贴空间不足的问题。上、下模分别铺贴完成后进行合模成型,采用整体共固化成型方法。这样,可以实现机身的承力要求,还可以达到结构减重30%的目的,为国内全复合材料主承力构件民机适航道路奠定基础,而且全复合材料共固化成型的机身无紧固件连接、无二次胶接,比照原有非整体化机身结构,减少工装数量100件以上,简化了整个工艺成型方法。This paper introduces the manufacturing method of the middle fuselage plenum of the light business jet. The middle fuselage is a semi-closed cabin. Considering the detachable mold of the formed parts, and the ease of processing and forming, the tooling cannot be made into a whole. It is manufactured by using the upper and lower parts to solve the problem of insufficient space for parts. After the upper and lower molds are respectively laid and finished, the mold is formed by a co-solidification molding method. In this way, the bearing capacity requirements of the fuselage can be achieved, and the structural weight reduction can be achieved by 30%, and the foundation for the civil airworthiness road of the domestic main bearing composite component is laid. Compared with the original non-integrated fuselage structure, the fuselage of the composite material is co-cured, no fastener connection, no secondary bonding, reducing the number of tooling more than 100, simplifying the entire process of molding.

关 键 词：增压舱 整体成型 共固化 复合材料工装 定位技术 过渡模 

分 类 号：V261[航空宇航科学与技术—航空宇航制造工程] TB33[一般工业技术—材料科学与工程]