This paper aims to develop an analytical method to predict the low-velocity impact response of simply supported stringer stiffened panels. Since the combination of stringer and panel provides aircraft structure with variable thicknesses, significant mathematical modelling is required to predict the transverse impact response of this type of designs. Within this analysis, the effect of variable stiffness distribution due to the stringer presence has been included. The performance of various layups is investigated to find the most suitable combination for panel-stringer laminate under impact loading. Analytical models were developed based on a spring-mass system to predict the dynamic behaviour of the striker-plate domain and, finally, determine the contact force history, which shows the main novelty of this research. Compared with Finite Element results, the model developed proved to successfully predict stringer stiffened composite panels' response with a range of layups and geometry designs under low-velocity impact loading conditions. The analytical results agree with the available data in the literature, and the error is less than 5%.

本文旨在开发一种分析方法，以预测简单支撑的桁架加劲板的低速冲击响应。由于纵梁和面板的组合为飞机结构提供了不同的厚​​度，因此需要大量的数学模型来预测此类设计的横向冲击响应。在此分析中，已包括由于存在纵梁而引起的可变刚度分布的影响。对各种铺层的性能进行了研究，以找到在冲击载荷下最适合面板纵梁层压板的组合。基于弹簧-质量系统开发了分析模型，以预测撞板区域的动态行为，并最终确定接触力的历史记录，这表明了这项研究的主要新颖性。与有限元结果相比，开发的模型被证明可以在低速冲击载荷条件下成功预测桁架加劲复合板在一系列铺层和几何设计中的响应。分析结果与文献中的可用数据相符，并且误差小于5％。