复合材料夹芯结构低速冲击性能研究  

Investigation on Low-velocity Impact Performance of Composite Sandwich Structure

作　　者：张轶群 王治邦 王长武[1] 郑锡涛[2] ZHANG Yiqun;WANG Zhibang;WANG Changwu;ZHENG Xitao(Nanjing Research Institute of Electronics Technology,Nanjing 210039,China;Institute of Aircraft Composite Structure,Northwestern Polytechnical University,Xi’an 710072,China)

机构地区：[1]南京电子技术研究所,江苏南京210039 [2]西北工业大学飞行器复合材料结构研究所,陕西西安710072

出　　处：《电子机械工程》2024年第2期1-5,29,共6页Electro-Mechanical Engineering

摘　　要：复合材料夹芯结构为电子设备与外层蒙皮提供了一体化设计的思路,可以大幅降低飞行器的结构重量。通过低速冲击试验和ABAQUS仿真研究了5 J和10 J冲击能量下某飞行器复合材料机翼蒙皮典型夹芯区域在低速冲击下的性能。随着冲击能量的增加,复合材料泡沫夹芯结构的能量吸收率由5 J的72.0%提升至10 J的76.0%。由仿真结果可知,当冲击能量达到10 J时,出现了纤维损伤,且损伤沿表层铺层角度扩展,基体压缩损伤主要出现在冲击正面,基体拉伸损伤主要出现在冲击背面,损伤随冲击能量的增加而变大。当冲击能量达到10 J时,上面板与泡沫芯体粘接处也产生了较大的损伤。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 

分 类 号：V258.3[一般工业技术—材料科学与工程]