建立了基于连续介质损伤力学的渐进失效模型以预测层合板的破坏, 分别考虑了纤维、基体的损伤破坏模式, 采用Cohesive单元模拟蒙皮和凸缘间的粘接, 结合二次应力准则及B-K准则预测界面的损伤起始及扩展;预测并对比分析了不同加载条件下, 帽型单筋板弯曲失效过程中的损伤扩展、破坏模式及破坏载荷.结果表明:加载点与试样线接触时, 帽型筋条顶部存在被压塌的风险;加载点与试样面接触有助于延缓帽顶的初始损伤, 获得更高的弯曲强度, 但无法避免加载过程中帽顶塌陷.%Four point bending failure behavior of single omega stiffened composite panel in typical aircraft structure was analyzed. A progressive failure analysis model based on continuum damage mechanics was established to predict the failure of laminates, damage modes of fiber and matrix were considered respectively. Cohesive element was used to simulate the bonding between skin and flange, damage initiation and propagation of the interface were predicted by combined the secondary stress criterion and B-K law. Then the damage propagation, failure modes and bearing behavior of single omega stiffened composite panel under four point bending with different loading conditions were predicted and analyzed.The result indicates that line contact mode is easy to trigger collapse of the cap, and surface contact mode can delay the initial damage of the cap and obtain higher bending strength, but cannot solve the problem of cap collapse during loading.
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