基于碳纳米纸传感器的玻璃纤维–铝合金层板结构监测

Structure Monitoring of Glass Fiber Aluminum Alloy Laminates Based on Buckypaper Paper Sensor

为了满足航空航天领域发展对材料高强度、低密度和高弹性模量,耐腐蚀性和抗疲劳等性能的需要,先进的铝合金和纤维增强复合材料凭借优异的性能在航空航天工业中得到广泛应用。本文利用碳纳米纸传感器分别布置在铝合金板、玻璃纤维板和GLARE板三组试件。传感器布置在铝合金表面和玻璃纤维板表面,在拉伸测试时电阻变化的拟合曲线几乎和位移–载荷曲线完全重合,可以准确地反映出玻璃纤维复合板的受载状况。GLARE板第三次拉伸实验力学性能稳定时,贴在铝合金以及玻璃纤维表面的1号和2号传感器电阻均随着载荷的增加而逐渐增加。而界面的3号和4号传感器电阻却没有出现随载荷的增加而出现类似于三角函数上下波动的趋势。当拉伸试验的最大载荷增加时传感器的灵敏度并未发生变化,通过传感器每次加载前的初始电阻判断其结构历史的最大受载,实现对GLARE板的受载监测。

To meet the increasing requirements of high strength, lowdensity, high elastic modulus, corrosion resistance and fatigue resistance ofmaterials in the aerospace industry, advanced aluminum alloys and fiberreinforced composites are widely used due to their excellent properties. Inthis paper, buckypaper sensors are arranged on three groups of specimens:aluminum alloy plate, glassfiber laminates and glass fiber reinforced aluminumlaminates (GLARE). The fitting curve of resistance change of buckypaper sensorsarranged on the surface of aluminum alloy plate and fiberglass laminates almostcoincides with load-displacement curve during tensile test. The load conditionof specimens can be accurately reflected. When the mechanical properties ofglass plate are stable in the third tensile test, the resistances of sensorsNo.1 and No.2 attached on the surface of aluminum alloy and glass fiberincrease gradually with the increase of load. However, the resistances ofsensors No.3 and No.4 did not fluctuate with the increase of load, which wassimilar to the fluctuation of trigonometric function. When the maximum load ofthe tensile test increases, the sensitivity of the sensor does not change. Themaximum load of the structure history is judged by the initial resistance ofthe sensor before each loading, so as to realize the load monitoring of glareboard.