在航空航天结构的局部损伤发展到危及结构的完整性和安全性之前，对其进行结构健康监测和损伤定位至关重要。为通过曲率模态法定位结构损伤，首先通过模拟计算验证该方法的可行性，并设置不同的信噪比的模态形状进行曲率模态法的敏感性分析。理论计算表明，曲率模态法对噪声比较敏感，信噪比低时会影响损伤检测的准确性。随后以真实含裂纹梁为对象，利用激光测振仪结合曲率模态法进行裂纹梁的损伤检测。为了使损伤检测结果更可靠，基于置信度定义了损伤阈值。实验结果表明：激光测振仪测量结果具有很高的信噪比，使得曲率模态法结合激光测振仪能够准确定位结构损伤，并且置信度超过99.9%。

Structural health monitoring and damage localization is critical before localized damage in aerospace structures develops to the point where integrity and safety are jeopardized. For this purpose, structural damage was localized by the modal shape curvature method. The feasibility of the method was firstly verified by simulation calculations, and the sensitivity analysis of the modal shape curvature method was carried out by setting mode shapes with different signal noise ratios. Theoretical calculations show that the modal shape curvature method is sensitive to noise, and the accuracy of damage detection is affected when the signal noise ratio is low. Subsequently, the laser vibrometer combined with the modal shape curvature method is used to detect the damage of cracked beams with real crack-containing beams. In order to make the damage detection results more reliable, a damage threshold is defined based on the confidence level. The experimental results show that the laser vibrometer measurements have a high signal noise ratio, and the modal shape curvature method combined with the laser vibrometer can accurately locate structural damage with a confidence level of more than 99.9%.