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Reduction of vibration by periodically stitched sandwich panel

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摘要 This work reveals that the addition of periodically distributed stitches to sandwich structure enables a significant reduction of vibration in stop-band and this new functionality is systematically investigated.Firstly,a finite element model which is capable of taking into consideration the three layers of the sandwich as well as the stitches is developed.The diagram of dispersion is calculated by applying Floquet-Bloch theorem to the boundaries of unit cell.With properly chosen properties of stitches,a stop-band for flexural wave is observed.This stop-band is further confirmed by the forced response of a large stitched sandwich panel under point excitation.The level of vibration in the stop-band is significantly reduced.The influence of the stitch rigidity and density on upper and lower limits of stop-band is also examined,which confirms that stitched sandwich can be tuned to mitigate vibration in a certain frequency band with appropriate stitch properties.These investigations have demonstrated the potential application of stitched sandwich in the area of vibration reduction.
出处 《Chinese Journal of Aeronautics》 SCIE EI CAS CSCD 2021年第7期39-49,共11页 中国航空学报(英文版)
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  • 1FU Hong-jun,MA Chong-qi,KUANG Nai-hang,LUAN Shi-lin.Interfacial Properties Modification of Carbon Fiber/Polyarylacetylene Composites[J].Chinese Journal of Aeronautics,2007,20(2):124-128. 被引量:8
  • 2Ilcewicz L B, Dost E F, Coggeshall R L. A model for compression after impact strength evaluation[A]. Proc of 21st International SAMPE Technical Conference[C]. 1989. 130-140.
  • 3Poe C C Jr. Demonstrating damage tolerance of composite airframes[R]. N94-29623, 1994.
  • 4Dost E F, Avery W B,Finn L B, Ilcewicz, L B, Scholz, D B, Wishart, R E. Impact damage resistance of composite fuselage structure [A]. Part 3. Fourth ACT Conference[C], 1993.
  • 5Yah Y. Analysis of impact threshold energy for fibre and fabric reinforced composites [J]. Journal of Reinforced Plastics and Composites, 1998, 17(12): 1056-1075.
  • 6Poe C C Jr. Mechanics methodology for textile preform composite materials [A]. Proc. of the 28^th International Technical Conference, SAMPE[C], 1996, 324-338.
  • 7Jackson W C, Poe C C Jr. The use of impact force as a scale parameter for the impact response of composite laminates[R]. N95-28479, 1995, 981- 998.
  • 8李勇,肖军,谭永刚,原永虎,党旭丹.X-cor夹层结构剪切模量实验与分析[J].南京航空航天大学学报,2008,40(6):831-835. 被引量:6
  • 9LI Chenghu,YAN Ying,WANG Ping,QI Desheng,WEN Yonghai.Study on Compressive Properties of Z-pinned Laminates in RTD and Hygrothermal Environment[J].Chinese Journal of Aeronautics,2012,25(1):64-70. 被引量:5
  • 10郑莹莹,李宁,尚伟,张向阳,胡晶晶,周小卫,肖军.K-cor增强泡沫夹层结构制备与力学性能[J].复合材料学报,2012,29(6):230-236. 被引量:4

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