Integrated Design and Validation of Composite Material Aircraft Fuselage Tooling
XUE Jijia1, LI He2, MA Shaohua2
1. Liaoning General Aviation Academy, Shenyang 110136, China;
2. College of Electromechanical Engineering, Shenyang Aerospace University, Shenyang 110136, China
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.
基金资助:辽宁省教育厅项目（L201611）；沈阳市科技计划项目（18–013–0–25）。
引用本文:
薛继佳，李鹤，马少华. 复合材料飞机机身工装模具一体化设计及验证[J]. 航空制造技术, 2019, 62(11): 97-101.
XUE Jijia, LI He, MA Shaohua. Integrated Design and Validation of Composite Material Aircraft Fuselage Tooling. Aeronautical Manufacturing Technology, 2019, 62(11): 97-101.
2019, 
