材料期刊网

随着复合材料的广泛使用，复合材料帽型加筋板在飞机结构上的使用也越来越多。为研究复合材料帽型加筋板承受轴向压缩的能力，首先对不同蒙皮半径、蒙皮厚度及长桁间距的复合材料帽型加筋板进行了轴压试验，得到了局部屈曲载荷、破坏载荷与加筋板曲率系数、长桁间距的关系，然后，通过引入曲率修正系数，修正了现有加筋板屈曲载荷的工程估算公式；最后，利用分段处理法结合有效宽度概念改进了加筋板轴压极限承载的工程算法。结果表明：帽型复合材料加筋板局部屈曲载荷及最终破坏载荷与曲率系数正相关；改进的方法能对复合材料加筋板的极限承载进行准确预测。所得结果表明该方法为复合材料加筋板结构设计及载荷估算提供了一种新方法，具有一定的工程应用价值。

As composite is widely adopted,more and more hat-stiffened composite panels are used in aircraft struc-tures.In order to investigate the loading capacity of hat-stiffened composite stiffened panel under axial compression, hat-stiffened composite panels with different radius of skin,thicknesses of skin and distances between adjacent stringers were tested under axial compression firstly.The relationships between local buckling load,collapse load and curvature coefficient of stiffened plate,distance of adjacent stringers were obtained.Then,by introducing cur-vature modifying coefficient,the existing buckling load formulation for engineering estimation of stiffened panel was modified.Finally,the engineering approach for ultimate load of stiffened plate under axial compression was modified using multistage operation method and combining effective width concept.The results show that local buckling load and ultimate collapse load of hat-stiffened composite panel are positive correlated with curvature coefficient.The modified method can predict the ultimate load of stiffened composite panel accurately.The conclusions obtained show that the modified approach can provide a new method for structural design and estimation for load of stiffened composite panel,which has definite engineering application values.