摘要
为了更好地满足飞机安全性、经济性、舒适性和环保性的需求,以碳纤维增强树脂基复合材料为代表的轻质高强先进材料在新一代大型客机机体结构中得到了大量应用。复合材料机身壁板具有不同于传统金属材料机身壁板的装配工艺特点,因此,其对装配协调提出了新的要求。首先,概述了飞机复合材料机身壁板的制造工艺,分析了复合材料机身壁板装配协调技术现状与面临的问题。其次,探讨了适用于复合材料壁板的装配协调方法,并提出了一种面向复合材料机身壁板装配力形协同控制的全主动驱动柔性装配协调方法。最后,通过仿真和物理实验验证了该方法的有效性,实现了复合材料机身壁板力形协同优化控制。
In order to meet the requirements of safety,economy,comfortability,and environmental protection,high specific strength advanced material,represented by carbon fiber reinforced plastics(CFRP),has been widely used in the airframe of the new generation commercial aircraft.CFRP composite fuselage panels have different assembly characteristics in comparison with traditional metal fuselage panels,which put forward new requirements for aircraft assembly.This paper firstly summaries the manufacturing process of composite fuselage panel,and analyzes the current status and problems of composite fuselage panel assembly.Then,the methods in composite fuselage panel assembly is discussed,and a fully-active-drive flexible assembly method for force/shape control of composite fuselage panel assembly is proposed.Finally,the feasibility and effectiveness of the proposed method are verified by simulation and physical experiments,with optimized control of force/shape control reached.
作者
李东升
杨应科
翟雨农
隋毅
LI Dongsheng;YANG Yingke;ZHAI Yunong;SUI Yi(School of Mechanical Engineering and Automation,Beihang University,Beijing 100191,China)
出处
《复合材料学报》
EI
CAS
CSCD
北大核心
2022年第9期4310-4318,共9页
Acta Materiae Compositae Sinica
基金
国家自然科学基金(52105502)
国家商用飞机制造工程技术研究中心创新基金(COMAC-SFGS-2019-263)。
