摘要
为研究玻璃纤维复合材料开孔以及充填孔对层合板压缩性能的影响,本文对填充孔、无孔和开孔的复合材料层合板进行了压缩实验。此外,采用两种不同材料和铺层建立了六种结构对应的三维有限元模型(FEM)用于损伤演化分析。结果表明,两种开孔试件的压缩强度比无孔试件分别降低了40.48%和31.34%;两种充填孔试件的压缩强度比开孔试件分别高54.55%和36.95%,仅略低于无孔试件。有限元计算得到的压缩强度与试验结果的误差仅为8.03%。仿真计算结果表明间隙配合均会降低充填孔结构的压缩强度;而对FH-2试件来说,当干涉量大于90μm时,同样也会降低充填孔结构的压缩强度。
In order to study the effect of glass fiber composites with holes and filled-holes on laminates,the no-hole(NH),open-hole(OH)and filled-hole(FH)compression experiments were carried out on the composite laminates.In addition,three-dimensional finite element models(FEM)corresponding to six kinds of structures were established by using two different materials and layers for damage evolution analysis.The results show that the compressive strength of the two kinds of open-hole specimens is 40.48%and 31.34%lower than that of the no-hole specimens;The compressive strength of the two filled-hole specimens is 54.55%and 36.95%higher than that of the open-hole specimens respectively,only slightly lower than that of the no-hole specimens.The error between the compression strength calculated by finite element method and the test result is only 8.03%.The simulation results show that the clearance will reduce the compressive strength of the filling hole structure;For FH-2 specimen,when the interference is greater than 90um,the compressive strength of the filled-hole structure will also be reduced.
作者
陈绍雄
刘磊
朱书华
周龙
王星雨
CHEN Shao-xiong;LIU Lei;ZHU Shu-hua(College of Aerospace Engineering,Nanjing University of Aeronautics and Astronautics,Nanjing 210016)
出处
《航空精密制造技术》
2023年第1期17-20,共4页
Aviation Precision Manufacturing Technology
关键词
玻璃纤维复合材料
充填孔压缩
渐进损伤分析
glass fiber composite
filled-hole compression
progressive damage analysis
