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夹层结构在飞机复合材料结构中大量使用,其连接处力学性能影响飞机结构的完整性。采用玻璃纤维板G10-t0.25“预埋于碳纤维材料面板纸窝芯的夹层结构中,针对20 mm、30 mm、40 mm等不同预埋件直径,开展拉脱试验。试验结果表明:较典型金属后埋件结构,拉脱载荷有较大提高,随着预埋件直径的增加,拉脱载荷不断增加;当预埋件直径大于30 mm后,预埋件直径的增加对拉脱载荷的提高影响不大。
The sandwich structure is extensively used in aircraft composite structures and the mechanical properties of the joints affect the structural integrity of the aircraft. Using glass fiber board G10-t0.25 ”embedded in the carbon fiber material sandwich panel core structure of the sandwich, for 20 mm, 30 mm, 40 mm diameter of the different embedding parts to carry out pull-off test results show that: With the increase of embedment diameter, the pull-off load increases with the increase of pull-off load. When the embedment diameter is more than 30 mm, the increase of embedment diameter has a significant effect on pull-off load Little effect of improvement.