Abstract Advanced composite laminated cylindrical shells are increasingly being desired in modern aerospace structures, for improving their structural efficiency and performance. In this paper, compared with the previous failure analysis, which considered buckling-failure only, a competitive failure analysis framework for composite laminated cylindrical shells is presented, in which linear buckling interacting curve method was considered for buckling-failure analysis and strength ratio based on Tsai-Wu failure criterion was used for stress-failure analysis. The proposed framework agreed well with the published data, which verified it’s feasibility. The competitive failure analysis of composite laminated cylindrical shells and parametric studies were conducted to reveal the failure mode. It is found that the higher ratios of longitudinal compressive strength to longitudinal modulus and shear strength to longitudinal modulus of composite materials, the more likely buckling-failure occurs; otherwise, stress-failure occurs. As the ratio of radius to thickness reduces, the possibility of occurrence of stress-failure increases. Moreover, the stress-failure for [90°/0°/90°] stacking sequence is more likely to occur than [θ/0°/θ], and 0°

中文翻译：

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复合材料层合圆柱壳在轴向压缩和扭转载荷作用下的屈曲和应力竞争失效分析

摘要 现代航空航天结构越来越需要先进的复合材料层压圆柱壳，以提高其结构效率和性能。本文与以往仅考虑屈曲-破坏的失效分析相比，提出了一种复合材料层合圆柱壳的竞争失效分析框架，其中考虑线性屈曲相互作用曲线法进行屈曲-失效分析，强度比基于Tsai-Wu 破坏准则用于应力破坏分析。提出的框架与公布的数据吻合良好，验证了其可行性。进行了复合材料层压圆柱壳的竞争失效分析和参数研究，以揭示失效模式。发现复合材料的纵向抗压强度与纵向模量和剪切强度与纵向模量的比值越高，越容易发生屈曲破坏；否则，就会发生应力失效。随着半径与厚度之比的减小，发生应力破坏的可能性增加。此外，[90°/0°/90°] 堆叠序列的应力失效比 [θ/0°/θ] 更容易发生，0°