The effect on curing deformation and strength of 90° plies in stringers for composite T-shaped stiffened panel were presented by numerical analysis and experimental measurement. In this work, the finite element model (FEM) for curing deformation based on cure kinetics formulation was utilized. The model for buckling and failure based on Tsai-Wu failure criteria and incremental/ Newton -Raphson mixed iteration equation was established. The curing, buckling and post-buckling analysis were performed on composite T-shaped stiffened panels to obtain the deformation, the critical load and mode of failure, with different 90° plies-ratios in stringers. Furthermore, the experimental investigation has been carried out for specimens with different plies-ratios of 90° plies in stringers. The good agreement between the numerical results obtained by finite element method and the experimental ones demonstrated that this kind of numerical analysis could estimate appropriately the behavior of the structure. In addition, it was found that the 90° plies in stringers play an important role in reducing the curing deformation, but it has little effect on the axial compression loading capacity for composite T-shaped stiffened panel, which is useful for application in civil aviation aircraft.

通过数值分析和实验测量，提出了对T形复合加筋板纵桁中90°帘布层的固化变形和强度的影响。在这项工作中，利用了基于固化动力学公式的固化变形的有限元模型（FEM）。建立了基于蔡-吴破坏准则和增量/牛顿-拉夫森混合迭代方程的屈曲与破坏模型。在T形复合材料加劲板中进行固化，屈曲和后屈曲分析，以得到变形，临界载荷和破坏模式，纵梁中具有不同的90°层-比率。此外，已经对具有不同层的试样进行了实验研究，纵梁中的90°层的比率。通过有限元方法获得的数值结果与实验结果之间的良好一致性表明，这种数值分析可以适当地估计结构的性能。此外，发现纵梁中的90°帘布层在降低固化变形方面起着重要作用，但对复合T形加劲板的轴向压缩载荷能力影响很小，这在民航中很有用飞机。