蜂窝芯体厚度对Nomex蜂窝夹层复合材料压缩性能的影响
Influence of Honeycomb Core Thickness on Compressive Property of Nomex Honeycomb Sandwich Composites
摘 要
以NRH-2-48芳纶纸为蜂窝芯体, 碳纤维层合板为面板, 制备了不同芯体厚度的Nomex蜂窝夹层复合材料, 通过压缩试验研究了芯体厚度对复合材料压缩性能的影响, 并探讨了芯体厚度与复合材料屈曲载荷和压缩破坏载荷的关系。结果表明: 随芯体厚度的增加, 复合材料的屈曲载荷和破坏载荷都相应增大, 当复合材料的屈曲载荷与面板的破坏载荷相同时, 蜂窝芯体厚度最佳。
芯体厚度
压缩性能
屈曲载荷
honeycomb sandwich composite
core thickness
compressive property
buckling load
Abstract
Nomex honeycomb sandwich composites with different core thickness were prepared using NRH-2-48 aramid paper as core and carbon fiber laminates as panels. The effect of core thickness on compressive property was studied by compression testing, and the relationships of core thickness with buckling load and compressive breaking load were investigated. The results show that with the increase of core thickness, the buckling load and the breaking load of the composite increased. When the buckling load of composites was as high as the breaking load of the panel, the core thickness was the best.
中图分类号 TB332
所属栏目 材料性能及其应用
基金项目
收稿日期 2013/9/22
修改稿日期 2014/8/1
网络出版日期
作者单位点击查看
备注董鑫(1987-), 男, 江苏徐州人, 硕士研究生。
引用该论文: DONG Xin,SHI Xiao-peng,CHANG Fei,WANG Xu. Influence of Honeycomb Core Thickness on Compressive Property of Nomex Honeycomb Sandwich Composites[J]. Materials for mechancial engineering, 2014, 38(10): 46～49
董鑫,石晓朋,常飞,王旭. 蜂窝芯体厚度对Nomex蜂窝夹层复合材料压缩性能的影响[J]. 机械工程材料, 2014, 38(10): 46～49
被引情况:
【1】虞文军,李飞,王东晔,张修瑞, "钛合金蜂窝瓦楞板的成形工艺",机械工程材料 40, 81-86(2016)
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参考文献
【1】董彦芝, 刘芃, 王国栋.航天器结构用材料应用现状与未来需求[J].航天器环境工程, 2010, 17(1): 41-45.
【2】KASSAPOGLOUS C, JONAS P J, ABBOTT R. Compressive strength of composite sandwich panel after impact damage: anex-perimental and analytical study[J].Journal of Composites Technology and Research, 1988, 10(2): 65-73.
【3】CAPRINO G, TETI, R. Impact and post-impact behavior of foam core sandwich structures[J].Composite Structures, 1994, 29: 47-55.
【4】程小全, 寇长河, 郦正能.复合材料蜂窝夹芯板低速冲击损伤研究[J].复合材料学报, 1998, 15(3): 124-128.
【5】VONACH W K, RAMMERSTORFER F G. Wrinkling of thick orthotropic sandwich plates general loading conditions[J]. Archive of Applied Mechanics, 2000, 70(5): 338-348.
【6】LEOTOING L, DRAPIER S, VAUTRIN A. Using new closed-form solutions to set up design rules and numerical investigations for global and local buckling of sandwich beams[J]. Journal of Sandwich Structures and Material, 2004, 6(3): 263-289.
【7】修英姝, 崔德刚.复合材料蜂窝夹层结构的优化设计[J].北京航空航天大学学报, 2004, 30(9): 855-858.
【8】张铁亮, 丁运亮, 金海波.基于有限元法的蜂窝夹层结构稳定性研究[J].复合材料学报, 2012, 29(3): 184-190.
【9】法洋洋, 陈秀华.蜂窝夹层结构拉脱破坏的有限元分析[J].机械工程材料, 2012, 6(10): 86-91.
【10】中国航空研究院.复合材料结构设计手册[M]. 北京: 航空工业出版社, 2001.
【2】KASSAPOGLOUS C, JONAS P J, ABBOTT R. Compressive strength of composite sandwich panel after impact damage: anex-perimental and analytical study[J].Journal of Composites Technology and Research, 1988, 10(2): 65-73.
【3】CAPRINO G, TETI, R. Impact and post-impact behavior of foam core sandwich structures[J].Composite Structures, 1994, 29: 47-55.
【4】程小全, 寇长河, 郦正能.复合材料蜂窝夹芯板低速冲击损伤研究[J].复合材料学报, 1998, 15(3): 124-128.
【5】VONACH W K, RAMMERSTORFER F G. Wrinkling of thick orthotropic sandwich plates general loading conditions[J]. Archive of Applied Mechanics, 2000, 70(5): 338-348.
【6】LEOTOING L, DRAPIER S, VAUTRIN A. Using new closed-form solutions to set up design rules and numerical investigations for global and local buckling of sandwich beams[J]. Journal of Sandwich Structures and Material, 2004, 6(3): 263-289.
【7】修英姝, 崔德刚.复合材料蜂窝夹层结构的优化设计[J].北京航空航天大学学报, 2004, 30(9): 855-858.
【8】张铁亮, 丁运亮, 金海波.基于有限元法的蜂窝夹层结构稳定性研究[J].复合材料学报, 2012, 29(3): 184-190.
【9】法洋洋, 陈秀华.蜂窝夹层结构拉脱破坏的有限元分析[J].机械工程材料, 2012, 6(10): 86-91.
【10】中国航空研究院.复合材料结构设计手册[M]. 北京: 航空工业出版社, 2001.
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