Abstract: With the rapid development of the low-altitude economy, flying vehicles have emerged as a design focus for next-generation transportation vehicles. Composite honeycomb sandwich panels, owing to their high specific strength and excellent flexural stiffness, have found extensive applications in this field. In this paper, quasi-static indentation tests are conducted on composite honeycomb sandwich panels to investigate their damage evolution, obtaining key data such as ultimate load, indentation depth, and damage area. Based on the experimental results, a finite element model of the composite honeycomb sandwich panel is established using numerical simulation to replicate the entire quasi-static indentation process. The validity of the computational model is confirmed through comparison with experimental data. Using this simulation model, the entire process from initial loading and damage initiation to damage evolution can be characterized. The results indicate that damage induced by quasi-static indentation first manifests as local crushing of the honeycomb core, leading to a reduction in its load-bearing capacity, which subsequently triggers initial damage in the face sheets. Therefore, the simulation approach can provide a basis for full-scale numerical simulations of flying vehicle wings.

Key words: honeycomb sandwich structure; quasi-static indentation; composite material; numerical simulation

摘要： 随着低空经济的快速发展，汽车飞行化成为新一代运载工具的设计热点。复合材料蜂 窝夹层板由于比强度高、抗弯刚度大在该领域得到广泛应用。文章针对复合材料蜂窝夹层板 开展了准静态压痕试验，研究了其损伤演化过程，获得了极限载荷、凹坑深度及损伤面积等 关键数据。在试验基础上，采用数值仿真方法建立了复合材料蜂窝夹层板的有限元模型，模 拟了准静态压痕试验的全过程，并通过与试验数据对比，验证了计算模型的有效性。利用该 仿真模型可以揭示从起始加载、初始损伤到损伤演化的全过程。结果表明，准静态压痕产生的 损伤先由蜂窝芯局部失稳，导致其承载能力下降，进而引发面板出现初始损伤。因此，仿真 方法能够为整车机翼的全尺寸仿真计算提供依据。

关键词: 蜂窝夹层结构；准静态压痕；复合材料；数值仿真