Impact resistance is one of the more critical and important features of composite materials used in the aerospace industry. The objective of work was to evaluate the hybrid titanium carbon laminate resistance to dynamic loads. The paper utilizes numerous criteria for evaluation of impact behaviour of materials, including force change, energy absorption characteristics and failure identification. To thoroughly analyze the damage mechanism, a detailed fractography of laminate destruction was performed. Moreover, an empirical model for determining the universal impact behaviour coefficient of fibre metal laminate (FML) was proposed. The first significant force fluctuations prove to reach the laminate’s impact resistance limit as caused by the initiation of cracking of respective layers and the consequent reduction of laminate rigidity. A growing proportion of absorbed energy in the case of growing impact energies, from some 50% in case of 2.5 J of energy, up to circa 80% in case of 30 J of energy was recorded. Reduction of interlayers with crossing fibers fosters the creation of cracks in the lower layer of titanium due to the limited capability of partial absorption of energy through delamination.

耐冲击性是航空工业中使用的复合材料的更关键和重要的特征之一。工作的目的是评估混合钛碳层压板对动态载荷的抵抗力。本文利用许多标准来评估材料的冲击行为，包括力变化，能量吸收特性和失效识别。为了彻底分析破坏机理，对层压板破坏进行了详细的分形。此外，提出了确定纤维金属层压板（FML）通用冲击行为系数的经验模型。最初的显着力波动证明已达到层压板的抗冲击极限，这是由于各层开始破裂并因此导致层压板刚度降低而引起的。记录到，在增加冲击能量的情况下，吸收能量的比例从2.5J能量的约50％增加到30J能量的约80％。由于通过分层部分吸收能量的能力有限，因此减少具有交叉纤维的中间层会促进在钛下层中产生裂纹。