Compression after impact properties of carbon-fiber/aluminum-honeycomb sandwich panels with short-Kevlar-fiber toughening
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摘要: 碳纤维夹芯板受到冲击载荷后易发生分层损伤，在工程应用中严重影响结构安全。首先对碳纤维/铝蜂窝夹芯板界面进行Kevlar短纤维增韧设计；其次对比研究了Kevlar短纤维界面增韧及未增韧夹芯板的低速冲击行为和冲击后压缩行为，将其冲击后剩余压缩强度、能量吸收及破坏模式进行对比；最后运用数字图像相关技术(DIC)获取增韧及未增韧试件在冲击后压缩过程中的应变云图。结果表明：低速冲击过程中，Kevlar短纤维增韧可以有效提高碳纤维/铝蜂窝夹芯板的冲击损伤阻抗，增韧试件的临界损伤阈值载荷明显高于未增韧试件；相比于未增韧试件，4种冲击能量下增韧试件的冲击后剩余压缩强度(CAI)值分别提高了2.68%、9.24%、4.65%、11.13%，能量吸收分别提高了69.09%、52.88%、55.03%、101.70%；对碳纤维/铝蜂窝夹芯板冲击后压缩过程中的DIC观测，进一步验证了芳纶短纤维对界面的增韧效果，并揭示了增韧界面对结构的增强机制。Abstract: Delamination between face sheets and core is one of the most common damage mode of carbon-fiber sandwich panels under impact loading, which seriously affects structural safety. Firstly, short-Kevlar-fibers were used for toughening the interface of carbon-fiber/aluminum-honeycomb sandwich panel. Secondly, low velocity impact and compression after impact tests were conducted for plain and toughened specimens. The residual compression strength, energy absorption and failure mode were compared. Finally, the strains of plain and toughened specimens during compression after impact test were obtained by digital image correlation (DIC). The results show that short-Kevlar-fiber toughening is capable to effectively increase the impact damage resistance of carbon-fiber/aluminum-honeycomb sandwich panel, and the damage threshold load of toughened specimens is signifi-cantly higher than that of plain specimens. Compared with the plain specimens, the residual compression strength values after impact of toughened specimens are increased by 2.68%, 9.24%, 4.65% and 11.13%, respectively, under four different impact energies. Meanwhile the energy absorption values of toughened specimens are increased by 69.09%, 52.88%, 55.03% and 101.70%, respectively. Furthermore, DIC observations were used to investigate the toughening effects of short-Kevlar-fibers and the strengthening mechanism.
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图 2 具有Kevlar短纤维增韧的碳纤维/铝蜂窝夹芯板
D—Diameter; h—Height; t—Thickness; b—Width; L—Length
Figure 2. Carbon-fiber/aluminum-honeycomb sandwich panel with short-Kevlar-fiber toughening
图 5 不同冲击能量下Kevlar短纤维界面增韧与未增韧碳纤维/铝蜂窝夹芯板的冲击力-时间曲线
Figure 5. Impact load-time curves of carbon-fiber/aluminum-honeycomb sandwich panels with and without short-Kevlar-fiber toughening under different impact energies
DTL—Damage threshold load
图 6 Kevlar短纤维界面增韧与未增韧碳纤维/铝蜂窝夹芯板在不同冲击能量下的临界损伤阈值载荷值
Figure 6. Damage threshold load of carbon-fiber/aluminum-honeycomb sandwich panels with and without short-Kevlar-fiber toughening under different impact energies
图 7 Kevlar短纤维界面增韧与未增韧碳纤维/铝蜂窝夹芯板在不同能量冲击后压缩过程中的载荷-位移曲线
Figure 7. Compressed load-displacement curves of carbon-fiber/aluminum-honeycomb sandwich panels with and without short-Kevlar-fiber toughening during compression after impact with different energies
图 8 Kevlar短纤维界面增韧与未增韧碳纤维/铝蜂窝夹芯板的剩余强度与吸能对比
CAI—Compression after impact
Figure 8. Comparison of residual strength and energy absorption of carbon-fiber/aluminum-honeycomb sandwich panels with and without short-Kevlar-fiber toughening
图 9 碳纤维/铝蜂窝夹芯板CAI破坏模式及短纤维增韧示意图：(a) 30 J冲击能量下未增韧和增韧试件CAI破坏模态；(b) Kevlar短纤维界面增韧示意图[25]
Figure 9. Schematic diagram of CAI failure mode of carbon fiber/aluminum honeycomb sandwich panel and sketch of the toughening effects: (a) CAI failure mode of carbon fiber/aluminum honeycomb sandwich panel with and without toughening under the impact energy of 30 J; (b) Sketch of the toughening effects with short Kevlar fibers[25]
图 10 20 J能量冲击后压缩过程中Kevlar短纤维界面增韧与未增韧碳纤维/铝蜂窝夹芯板在X与Y方向的工程应变曲线
Figure 10. Engineering strain curves of carbon-fiber/aluminum-honeycomb sandwich panels with and without short-Kevlar-fiber toughening in X and Y directions under the impact energy of 20 J
表 1 不同冲击能量下Kevlar短纤维界面增韧碳纤维/铝蜂窝夹芯板面板破坏形貌
Table 1. Failure morphologies of carbon-fiber/aluminum-honeycomb sandwich panel with short-Kevlar-fiber toughening under different impact energies
Impact energy/J 10 20 30 50 Top surface 
Bottom surface 
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表 2 Kevlar短纤维界面增韧与未增韧碳纤维/铝蜂窝夹芯板在20 J能量冲击后压缩过程中不同压缩应变对应的工程应变云图
Table 2. Engineering strain nephograms of carbon-fiber/aluminum-honeycomb sandwich panels with and without short-Kevlar-fiber toughening at different compression strain under the impact energy of 20 J
Engineering strain Plain specimen Toughened specimen $ \varepsilon $ =0.002 $ \varepsilon $ =0.005 $ \varepsilon $ =0.008 $ \varepsilon $ =0.002 $ \varepsilon $ =0.005 $ \varepsilon $ =0.008 $ {\varepsilon }_{YY} $ 
$ {\varepsilon }_{XX} $ 
$ {\varepsilon }_{XY} $ 
Notes: $ { \varepsilon } $—Average compression strain; $ {\varepsilon }_{YY} $—Engineering strain in Y direction; $ {\varepsilon }_{XX} $—Engineering strain in X direction; $ {\varepsilon }_{XY} $—Shear strain.
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