Patch Repair and Structural Health Monitoring of Fatigue-Cracked Aging Aircraft Panels

为了延长老化飞机的使用寿命，迫切需要发展老化飞机结构的修复技术。本课题从飞机壁板修复后结构健康监测的角度出发，对纤维增强复合材料补片修补技术进行了研究。主要研究成果如下：1.基于二维有限元和三维有限元/边界元相结合的方法，提出了FRP复合材料贴片修补飞机结构板疲劳裂纹扩展行为的数值模拟方法。2.提出了识别修补后飞机结构板疲劳裂纹和脱粘前缘的位置和形状的方法。3.研制了安装在贴片表面的光纤布拉格光栅(FBG)传感器应变测量传感器系统。4.基于非线性数学规划方法，建立了基于光纤布拉格光栅(FBG)传感器的应变测量传感器系统。开发了玻璃钢复合材料补片的设计系统。5.研究了修补技术在实际应用中存在的问题，并进行了可行性研究。

Developing the repair technology of aging aircraft structures has been desired to extend the service life of aging aircraft. In this research project, the repair technology using bonded fiber-reinforced polymer (FRP) composite patches has been investigated from the viewpoint of structural health monitoring of repaired aircraft structural panels. The main results are summarized as follows :1.Based on a two-dimensional FEM and a three-dimensional combined FEM/BEM, the numerical simulation method of the fatigue crack growth behavior in cracked aircraft structural panels repaired with a bonded FRP composite patch was presented.2.The method for identifying the locations and shapes of fatigue crack and disbond fronts in repaired aircraft structural panels was presented.3.The strain measuring sensor system using fiber Bragg grating (FBG) sensors installed on the patch surface was developed.4.Based on a nonlinear mathematical programming method, the design system of the FRP composite patches was developed.5.The issues in practical use of repair technology were examined, and the feasibility study was made.