中文摘要：

针对民用航空器用玻璃纤维增强环氧树脂基复合材料（GFRP，glassfiber reinforoe polymer）层合板，典型损伤通常采用挖补方法进行修理。本研究对挖补修理的关键参数——台阶比率、表面粗糙度、固化温度等因素对挖补修理结构拉伸性能的影响规律进行了系统研究。实验结果表明，挖补修理明显改变了GFRP层板结构的力学特性，在6种台阶比率（1：10～1：60）中，随着台阶比率的增加，拉伸强度呈现先增加后减小的趋势，在台阶比率为1：40时，拉伸强度最高，拉伸强度保持率约为51％。在台阶比率为1：40情况下，修理试样拉伸强度随着粘接界面的粗糙度增加而增加；同时，随着修理固化温度的增加，拉伸强度也出现先增加后降低的趋势．250下时修理试样拉伸强度最高。

英文摘要：

Scarf repair approach is usually adopted to deal with a typical damage in GFRP （glass fiber reinforce polymer） laminate on a civil aviation aircraft. A systematic research is conducted on the influence of scarf repair key parameters such as step ratio, surface roughness and curing temperature upon its tensile properties. Experimental results reveal that scarf repair approach has a significant changing effect on the mechanical properties of GFRP laminated plate structure. Along with the increase of step ratio （from 1：10 to 1：60）, the tensile strength appears a trend of decrease following an initial increase. When step ratio is 1：40, the tensile strength reaches its peak, with a tensile strength retention rate of 51%. In the case of 1：40 step ratio, the tensile strength of repair specimen increases with an intensity of roughness on the surface of junction. Meanwhile, with the increase of curing temperature, tensile strength also presents a trend of increase after a decrease and the tensile strength of repair specimen reaches its maximum when the temperature is 250 °F.