In this paper, experimental studies on two laminated composite hat-stiffened panels with equally spaced stiffeners have been carried out with application of axial compression load on the panel for the determination of the pre-buckling and post buckling behavior. A non-linear buckling analysis on the hat-stiffened panel has also been performed under compression load with application of finite element tool ABAQUS. From strain analysis at different locations, the local buckling of skin has been observed before the buckling of the panel, and a visual damage has been found near the skin-stiffener and debonding skin-stiffener of the panel during failure of the hat-stiffened panel. The compression load-axial displacement curve of the experiments has correlated well with simulated finite element model result for determination of the buckling behavior of the panel up to the failure load. The out of plane displacement pattern shows that the compressive failure initiated at the edges of the panel and gone to skin-stiffener bonding, and finally failure of the panel occurred due to debonding between skin-stiffener.

在本文中，已经在具有相等间隔的加劲肋的两个层压的复合帽形加劲板上进行了试验研究，并在板上施加了轴向压缩载荷，以确定屈曲前后的行为。还使用有限元工具ABAQUS在压缩载荷下对帽子加筋板进行了非线性屈曲分析。根据不同位置的应变分析，在面板弯曲之前观察到了局部的皮肤弯曲，并且在帽子加硬面板失效期间，在面板的皮肤加劲剂和剥离的皮肤加劲剂附近发现了视觉损伤。实验的压缩载荷-轴向位移曲线与模拟有限元模型结果具有很好的相关性，用于确定面板直至破坏载荷的屈曲行为。平面外位移模式表明，压缩破坏在面板的边缘处开始，并开始与蒙皮-加劲剂粘合，最后面板的破坏是由于蒙皮-加劲剂之间的脱粘而发生的。