复合材料机身帽型长桁加筋壁板剪切失稳及张力场计算

摘 要 碳纤维复合材料逐渐大量应用于大型民机机身设计，本文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。

Calculation of shear instability and diagonal tension of composite fuselage hat-stringer panel

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 are studied by analysis and experiment in this paper. The shear load test of fuselage panel is completed using the advanced multi-load panel test equipment, the instability mode and load, failure mode and load of the panel are obtained. The shear instability characteristics of fuselage panel are studied by engineering method and finite element eigenvalue method respectively. The shear failure characteristics of composite panels are studied by the diagonal tension analysis method. Finally the shear instability analysis method is 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.