In this paper, a parametric numerical study is performed on the sandwich composite leading edge to analyse the effect of skin thickness, layups, impact velocities to compare the performance of the two different reinforcements within sandwich leading-edge structures. The detailed numerical analysis of a composite leading edge reinforced with honeycomb and foam is developed using explicit finite element software, LS-DYNA. Initially, the study proposes the most suitable equations of state for impact on the metallic leading edge for different bird geometries made from Lagrangian and SPH methods. All the numerical results are verified with available experimental data in the literature. The results will deliver a cost-efficient and accurate numerical model which assists aircraft designers in deciding the combination of design variables resulting in improved impact resistance for sandwich aircraft structures under soft body impacts.

在本文中，对夹芯复合材料前缘进行了参数数值研究，以分析蒙皮厚度，叠层，冲击速度的影响，以比较两种不同增强材料在夹芯前缘结构中的性能。使用显式有限元软件LS-DYNA开发了蜂窝和泡沫增强的复合材料前缘的详细数值分析。最初，研究提出了由拉格朗日法和SPH法制成的不同鸟类几何形状对金属前沿产生影响的最合适的状态方程。所有数值结果均通过文献中可用的实验数据进行了验证。