面向低空飞行器服役过程中频发的低速冲击威胁，探明复合材料夹芯部件在多次冲击下的损伤累积与承载退化机理，对于提升低空飞行器复合材料部件的损伤容限设计具有重要意义。本文以编织/单向混杂复合材料蜂窝与泡沫夹芯平板为研究对象，系统开展了多次低速冲击及冲击后压缩试验研究。重点分析了编织/单向混杂蜂窝与泡沫两种典型夹芯平板在多次连续冲击下的动态力学响应特征与能量耗散规律，研究了面板堆叠顺序对混杂夹芯结构多次冲击下损伤形式与吸能特性的影响，揭示了含损夹芯平板剩余承载能力退化规律与损伤形式。研究结果表明：编织层能有效分散载荷并抑制微裂纹扩展。蜂窝与泡沫芯材构型主导了多次冲击下的损伤累积规律，进一步决定了复材夹芯结构在压缩载荷下失稳演化与塌陷模式。蜂窝夹芯在多次冲击下发生剪切冲塞破坏，在冲击后压缩加载下出现横向撕裂裂纹，而泡沫夹芯通过压溃密实呈现压缩-剪切耦合的压陷失效模式。本研究为低空飞行器机身结构抗多次冲击设计与损伤容限评估提供工程设计依据。

Addressing the threat of frequent low-velocity impacts during the service of low-altitude aircraft, clarifying the mechanisms of damage accumulation and load-bearing degradation in composite sandwich structures is of great significance for enhancing their damage tolerance design. This study focuses on woven/unidirectional (UD) hybrid composite sandwich panels with honeycomb and foam cores, systematically conducting repeated low-velocity impact and compression-after-impact (CAI) experiments. The research primarily analyzes the dynamic mechanical responses and energy dissipation patterns of these two typical sandwich configurations under consecutive impacts. Furthermore, the influence of face sheet stacking sequences on the damage modes and energy absorption characteristics is investigated, revealing the degradation laws of residual load-carrying capacity. The results demonstrate that the woven layers effectively distribute impact loads and suppress micro-crack propagation. The core configuration governs the damage accumulation laws, which further dictates the buckling evolution and collapse modes of the composite sandwich structures under compressive loading. Specifically, the honeycomb sandwich structures undergo shear plugging failure under repeated impacts and exhibit transverse tearing cracks during subsequent CAI loading. In contrast, the foam cores exhibit a compression-shear coupled indentation failure mode through localized crushing and densification, offering superior residual load-carrying capacity compared to the honeycomb structures. This research provides a critical engineering basis for the anti-impact design and damage tolerance assessment of composite sandwich fuselage structures for low-altitude aircraft.