复合材料曲板在民用大型飞机结构中有着广泛运用，准确预测和掌握复合材料曲板后屈曲行为对飞机结构安全性与结构减重优化具有重要意义。提出了一种基于双三角级数的正交铺层复合材料曲板后屈曲挠度解析解，考虑了初始几何缺陷和挠曲波峰偏移现象对曲板后屈曲行为的影响，通过伽辽金法得到压缩载荷与挠曲位移的非线性关系。采用T300/EPW碳纤维预浸料制备了无量纲曲率10.0~15.0的复合材料曲板试验件，利用压缩后屈曲试验结果和粒子群算法校准和优化了本文提出的解析预测方法，总体误差小于7%。

Curved composite panels are widely used in civil aircraft structures. Accurate prediction and understanding of their post-buckling behaviors are of great significance for ensuring structural safety and weight reduction. This study proposes an analytical solution for the post-buckling of cross-ply curved composite panels based on a double trigonometric series, which accounts for the effects of initial geometric imperfections and the phenomenon of crest shift. The nonlinear relationship between compressive load and deflection are derived using the Galerkin’s method. Experiment specimens of curved composite panels with dimensionless curvatures ranging from 10.0 to 15.0 are fabricated using T300/EPW carbon fiber prepreg. The analytical prediction method proposed in this study is calibrated and optimized through post-buckling compression tests and particle swarm optimization algorithms, demonstrating an overall error of less than 7%.