In this paper, a non-contact non-destructive evaluation of cumulative fatigue damage in $75\mathrm{\mu }\mathrm{m}$-thick aluminum plates is conducted by using the first symmetric zero-group-velocity Lamb mode and taking benefit of its local and long-lasting resonance feature. The tested aluminum sheets are subjected to fatigue loading, in a two sides clamped compression configuration inducing buckling. For understanding the experimental observations, we propose and establish an empirically-inspired theoretical modeling based on the cumulative damage theory, completed with a finite element simulation, for comparison with the experimental measurements. The observed phenomena along fatigue cycles show the potential for the prediction of the fatigue lifetime and the quantitative assessment of different stages of the fatigue damage in solid plate structures. Good agreement is found between the proposed theory/simulation and the experiment on zero-group-velocity resonance frequency. The quality factor of zero-group-velocity resonance is also experimentally studied and compared with numerical calculations, a disagreement is observed after $\sim$30% of fatigue lifetime. This point elucidates the start time of the change of mechanical properties during the early fatigue stage and is identified as a potential path for the improvement of the proposed empirical model in the future.

本文通过非接触非破坏性方法评估了累积疲劳损伤 $75\mathrm{\mu }\mathrm{米}$厚铝板是通过使用第一个对称零族速度Lamb模式进行的，并利用了其局部和持久的共振特性。被测试的铝板承受疲劳载荷，处于两侧夹紧的压缩结构中，从而引起屈曲。为了理解实验观察结果，我们提出并建立了基于累积损伤理论的经验启发理论模型，并以有限元模拟完成，以与实验测量结果进行比较。沿疲劳周期观察到的现象显示出了预测疲劳寿命和定量评估固态板结构疲劳损伤不同阶段的潜力。所提出的理论/仿真与零群速度共振频率的实验之间找到了很好的一致性。还通过实验研究了零群速度共振的品质因数，并与数值计算进行了比较，观察到$〜$疲劳寿命的30％。这一点阐明了疲劳早期阶段力学性能变化的开始时间，并被确定为将来改进所提出的经验模型的潜在途径。