航空复合材料短柱加筋板压缩性能试验研究

EXPERIMENTAL STUDY ON THE COMPRESSIVE PERFORMANCE OF AERO SHORT-BEAM COMPOSITE STIFFENED PANEL

开展了航空复合材料短柱加筋板的轴向压缩试验。试验件的破坏形式主要包括壁板的撕裂、筋条的断裂和端部的压溃现象,试验过程中,壁板及筋条没有出现明显的脱粘现象。在试验加载初期,载荷-应变曲线呈线性一致的增加趋势,位移测量点的离面位移值基本保持在0 mm附近;当压缩载荷超过临界屈曲载荷时,载荷-应变曲线出现了明显的分岔现象,且离面位移值快速增加。复合材料短柱加筋板失稳后仍然具有后屈曲承载能力,但是该承载能力较小,当短柱加筋板发生失稳后,随着压缩载荷的增加,试验件会很快发生破坏。有限元仿真结果与试验结果较一致,仿真结果表明短柱加筋板主要发生了壁板的局部失稳。

Compressive experiment on the aero short-beam composite stiffened panel was carried out in this paper. The fracture of stiffeners and splitting of panels as well as the failure of either ends are involved in the failure modes. However,the debonding of stiffeners to panels does not appear. At the beginning of loading history,the load-strain curve exhibits linear increasing trend while the out-of-plane displacements are around 0 mm. When the compressive loads exceed the critical buckling load,the strain-load curve tends to branch off. At the same time,there is a drastic rise in the displacement-load curve. The results indicate that short-beam composite also exhibits the post-buckling carrying capacity,which is relatively small. The failure occurs very soon in the short-beam composite stiffened panels if the buckling phenomenon occurs. The results obtained by FE software is consistent with the experimental results. The finite element results indicate that the buckling modes of specimens is the local buckling of panel between stiffeners.