The safe exploitation of the buckling and post-bulking region of stiffened composite panels is of prime interest in aerospace engineering. Experiments were carried out to investigate the effects of stringer design on the buckling and post-buckling behavior of stiffened composite panels subjected to in-plane shear loading in this study. Three configurations of I-shape stringers were designed with the same skin in the stiffened composite panels. The shear loading was applied through a customized picture-frame rig which is loaded by a mechanical test machine. Ten specimens in total were manufactured and tested to obtain the buckling loads and the final failure loads, respectively. The experimental results show that the stringer design has much more influence on the buckling load than the final failure load of the stiffened composite panel.

安全开发加硬复合板的屈曲和后膨胀区域在航空航天工程中至关重要。在本研究中，进行了实验以研究纵梁设计对加筋复合板在平面内剪切载荷作用下的屈曲和屈曲后行为的影响。在加硬的复合面板中设计了具有相同蒙皮的三种I型桁条构型。剪切载荷是通过定制的相框钻机施加的，该钻机由机械测试机加载。共制造并测试了十个试样，分别获得了屈曲载荷和最终破坏载荷。实验结果表明，桁条设计对屈曲载荷的影响要大于加劲复合板的最终破坏载荷。