复合材料机身壁板的强度分析与试验验证  

Strength analysis and test verification of composite fuselage panels

作　　者：李真[1] 王俊[1] 邓凡臣[2] 于振波[1] LI Zhen;WANG Jun;DENG Fanchen;YU Zhenbo(Shanghai Aircraft Design and Research Institute,Shanghai 201210,China;China Aircraft Strength Research Institute,Xi'an 710065,China)

机构地区：[1]上海飞机设计研究院,上海201210 [2]中国飞机强度研究所,西安710065

出　　处：《航空学报》2020年第9期118-130,共13页Acta Aeronautica et Astronautica Sinica

基　　金：民机科研项目(MJ-2015-F-038)。

摘　　要：复合材料在大型客机机身主承力结构应用是近年来的发展趋势,通过分析与大型壁板试验结合的方式研究了复合材料机身壁板的静力承载能力,以及疲劳与损伤容限特性。采用理论公式、半经验公式、有限元模态分析研究了蒙皮的屈曲载荷、壁板的承载能力。依靠创新的机身壁板多轴载荷试验系统,模拟机身壁板的实际受载情况,实现充压载荷、拉伸/压缩、剪切载荷的独立施加与组合施加。通过静力试验验证蒙皮屈曲的工程及有限元分析方法和壁板的剩余强度承载分析方法。引入预埋缺陷、BVID、VID冲击损伤,通过试验研究了损伤对应变分布的影响,并通过疲劳、损伤容限试验,验证了壁板的设计以及损伤的无扩展特性。The application of composite materials in the main loading structure of the aircraft fuselage is the development trend in recent years.In this paper,the static loading capacity,fatigue and damage tolerance characteristics of composite fuselage panels are analyzed with large-scale panel test.The buckling load of skin and the loading capacity of panel are examined by adopting the theoretical formula,the semi empirical formula,and the finite element modal analysis.The advanced multi-load panel test rig is used to simulate the actual loads of fuselage panel,achieving the independent and combined application of the pressure,tension,compression,and shear load.The engineering and finite element analysis method of skin buckling and the residual strength loading analysis method of panel are verified by static tests.By introducing the embedded defect,BVID and VID damage,the influence of the damage on strain distribution is studied by experiment,and the non-expansion property of the damage is verified by fatigue and damage tolerance experiments.

关 键 词：复合材料 机身壁板 稳定性 疲劳 损伤容限 

分 类 号：V223[航空宇航科学与技术—飞行器设计]