模态应变能在复合材料机翼结构损伤检测中的应用

DAMAGE DETECTION OF COMPOSITE WING BY USING MODAL STRAIN ENERGY

以复合材料机翼结构为研究对象,采用单元模态应变能改变率作为结构损伤标识量,对损伤结构进行损伤识别仿真。应用NASTRAN有限元程序对模型进行模态分析,模态分析的结果表明,单元模态应变能改变率对不同位置和不同程度损伤都具有较强的敏感性。应用神经网络成功识别了损伤的位置和程度,指出其可行性。

Damages at composite wing are simulated. Vibration mode analysis is by using commercial finite element software, and the analysis shows the sensitivity of the change ratio of the element modal strain energy to the location and severity of structure damage. Hereby, the change ratio of the element modal strain energy is presented as the indicator for structure damage detection. A successful identification of the location and severity of a structure damage is achieved by using artificial neural network.