摘要
碳纤维复合材料逐渐大量应用于大型民机机身设计,通过分析和试验的方法研究了复材机身单曲率壁板在剪切载荷下的失稳及破坏特性。采用先进的大型机身壁板试验设备完成单曲率壁板的剪切载荷试验,得到壁板的失稳模态和失稳载荷、破坏模式和破坏载荷。采用不同边界的工程方法和有限元特征值方法研究了机身壁板的剪切失稳特性。采用剪切张力场分析方法研究复材壁板的剪切破坏特性。最后通过试验结果完善了剪切失稳分析方法,验证了剪切张力场分析方法,为复材机身壁板的设计分析提供支持。
Carbon fiber reinforced polymer(CFRP)has been widely used in the design of large civil aircraft fuselage panels.The instability characteristics and diagonal tension characteristics of composite fuselage panel with single curvature under shear load were studied by analysis and experiment.The shear load test of fuselage panel was completed using the advanced multi-load panel test equipment,the instability mode and load,failure mode and load of the panel were obtained.The shear instability characteristics of fuselage panel were studied by engineering method and finite element eigenvalue method respectively.The shear failure characteristics of composite panels were studied by the diagonal tension analysis method.Finally the shear instability analysis method was perfected through the test results,and the diagonal tension analysis method is verified,which provides support for the design and analysis of composite fuselage panel.
作者
李真
程立平
李卫平
LI Zhen;CHENG Li-ping;LI Wei-ping(Commercial Aircraft Corporation of China, Shanghai Aircraft Design and Research Institute, Shanghai 201210, China;Aviation Industry Corporation of China, China Aircraft Strength Research Institute, Xi'an 710065, China)
出处
《科学技术与工程》
北大核心
2021年第23期10080-10085,共6页
Science Technology and Engineering
基金
民机科研项目(MJ-2015-F-038)。
关键词
复合材料
机身壁板
剪切失稳
张力场分析
composite material
fuselage panel
shear instability
diagonal tension analysis
