复合材料层板冲击后压缩强度经验预测公式

复合材料被广泛应用于飞机结构中，其损伤容限性能是飞行器设计的重要指标。提出了一种基于冲击能量预测复合材料层板受冲击后剩余压缩强度的经验预测公式，并通过试验方法分析了剩余强度的影响因素，确定了经验公式形式与参数，对经验公式预测结果进行了验证。经过一定量的试验验证，本文所提出的经验预测方法的预测结果与试验结果吻合良好，研究结果表明，该方法是一种简便迅速的剩余强度工程预测方法。试验结果表明：剩余强度与冲击能量的关系适合采用分段幂函数进行拟合；冲击能量、层板厚度、铺层比例和韧性对复合材料层板冲击后压缩强度有较明显的影响，而冲头直径对剩余强度的影响不显著。

An empirical prediction formula for compressive strength of composite laminates after impact

Composites are widely used in the aircraft structure and its damage tolerance property is an important index of aircraft design. An empirical prediction formula for compressive strength of composite laminate after impact based on energy was formulated. With experimental studies, influence factors for compressive strength were analyzed to determine the forms and parameters of the empirical formula, and the predicted results were compared with experimental data as well. The predicted results of the empirical method accord well with sufficient experimental data by general verification. The results indicate that it is a convenient and efficient engineering prediction method for compressive strength after impact. In addition, the experimental results indicate that the relationships between compressive strength and impact energy are suitable for piecewise power function fitting. Impact energy, thickness of laminate, ply proportion and material tenacity have obvious effect on compressive strength of composite laminate after impact, while the diameter of impactor has no significant effect.