The composite sandwich structure provides an integrated design approach for electronic device and outer skin,which can significantly reduce the structural weight of aircraft.The performance of the typical sandwich area of the composite wing skin of an aircraft under low-velocity impact when the impact energy is 5 J or 10 J is studied through low-velocity impact tests and ABAQUS simulation.With the increase of impact energy,the energy absorption ratio of composite foam sandwich structure increases from 72.0%of 5 J to 76.0%of 10 J.According to the simulation results,when the impact energy reaches 10 J,fiber damage occurs,and the damage extends along the surface layer angle.The matrix compression damage mainly occurs on the impact front side,while the matrix tensile damage mainly occurs on the impact back side.The damage increases with the impact energy.When the impact energy reaches 10 J,the joint between the upper panel and the foam core also shows significant damage.
关键词
飞行器/电子设备/复合材料泡沫夹芯结构/低速冲击/有限元分析
Key words
aircraft/electronic devices/composite foam sandwich structure/low-velocity impact/finite element analysis
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