摘要
针对RX1E复合材料轻型飞机一体成型、胶结连接为主的工艺特性,进行了工艺方案的总体设计,包括装配顺序的确定和装配工装基准的选择等。其次,进行了一体化工装的结构设计,细化了制件模具的成型方案和结构零件的定位夹紧形式。最后,重新进行了尾翼、阻力板等较小部件制造,对一体化工装的实际使用进行了验证,类比分析了工装模具一体化的方案在复合材料结构轻型飞机机身上的技术可行性和先进性。研究成果可为复合材料飞机工装提供设计思路和参考。
Aiming at the process characteristics of integral forming and cementing connection of light composite material aircraft, the overall design of the process scheme was carried out. It included the determination of assembly order,the choice of assembly tooling benchmarks. Then, the integration of the tooling structure is designed, refinement of the mold forming and positioning and clamping of the structural parts are also studied. Finallly, small parts like tail, drag plate are manufactured again. The practical use of integrated tooling is verified, meanwhile the feasibility and advancement of integrated tooling design on light composite material aircraft fuselage is verified by analogy analysis. The study can provide reference for design of composite material aircraft.
作者
薛继佳
李鹤
马少华
XUE Jijia;LI He;MA Shaohua(Liaoning General Aviation Academy,Shenyang 110136,China;College of Electromechanical Engineering,Shenyang Aerospace University,Shenyang 110136,China)
出处
《航空制造技术》
2019年第11期97-101,共5页
Aeronautical Manufacturing Technology
基金
辽宁省教育厅项目(L201611)
沈阳市科技计划项目(18–013–0–25)
