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为确定翼肋支撑对复合材料加筋板轴压性能的影响,对施加翼肋支撑前后的复合材料工型加筋板和帽型加筋板进行压缩试验和数值模拟研究。轴压试验中,通过应变计和影像云纹法实时监测试验件的失稳载荷及失稳模态,通过断面观测分析结构损伤破坏机制。基于ABAQUS软件建立有限元模型模拟加筋板屈曲及后屈曲过程,通过失稳节线及反节线上的应力分布变化分析加筋板破坏机制。计算结果与试验结果相吻合,表明翼肋支撑对不同筋条加筋板失稳模态有影响但均不改变结构失稳载荷,位于节线上的翼肋支撑对工型加筋板破坏载荷影响较小,但位于反节线上的翼肋支撑使帽型加筋板的承载能力提高了26.2%。试验件失稳后应力向反节线上筋条蒙皮界面集中,过高的应力导致界面脱粘,使得结构集中在反节线上破坏。
In order to determine the effect of rib support on the axial compressive properties of composite stiffened plates, the compression tests and numerical simulations of composite stiffener plates and hat stiffened plates before and after the application of rib support were carried out. In the axial compression test, the load and the instability mode of the test piece are monitored in real time through strain gage and moiré method, and the damage mechanism of the structural damage is analyzed through the sectional observation. The finite element model was established based on ABAQUS software to simulate the buckling and post-buckling of stiffened plate. The failure mechanism of stiffened plate was analyzed by the change of stress distribution on the buckling and anti-pitch lines. The calculated results are in good agreement with the experimental results. It shows that the rib support has influence on the failure modes of stiffened plates with different rib stiffeners but does not change the structural buckling load. However, the rib support located on the anti-pitch line increased the carrying capacity of the hat stiffener by 26.2%. After instability of the test piece, stress is concentrated on the stiffener skin interface on the anti-pitch line. Excessive stress leads to debonding of the interface, so that the structure is concentrated on the anti-pitch line and damaged.