缝合复合材料层板面内边缘冲击及冲击后压缩实验

doi:10.11896/cldb.21050254

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Abstract Stitched and unstitched carbon fiber reinforcedplastic (CFRP) laminates were manufactured by the vacuum assisted resin transfer molding(VARTM) technique and subjected to in-plane edge impact and compression after impact under five different energies. The damage after edge impact inside the structure was detected by the ultrasonic C-scan method. The experimental results show that stitching can improve the edge-impact resistance and damage tolerance of the laminates effectively. Within the impact energy range tested, the peak impact force increased by 4.54%～10.33% and the maximum increase of the residual compressive strength after impact was 9.32%. In addition, through the result from ultrasonic C-scan, it is found that there was a semi-elliptical delaminated damage area near the impact edge on the composite plates after in-plane edge impact of the structures, and the damage area of the stitched laminates was significantly smaller than that of unstitched. The main compression failure mode after in-plane edge impact of the unstitched laminates was delamination propagation, while the stitched laminates was global buckling.

Key words： stitching in-plane edge impact compression after impact ultrasonic C-scan

Published: Online: 2022-12-09

CLC number:

TB332

Fund:National Natural Science Foundation of China (51763016,51875201) and the Innovation Fund Designated for Graduate Students of Jiangxi Province (YC2020-S090).

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	Articles by authors
	LI Meiyan
	LAI Jiamei
	MO Mingzhi
	LUO Zhiqiang
	HUANG Zhichao

Cite this article:

LI Meiyan,LAI Jiamei,MO Mingzhi, et al. Experimental Investigation of Stitched Composite Laminates Subjected to In-plane Edge Impact and Compression After Impact[J]. Materials Reports, 2022, 36(23): 21050254-6.

URL:

http://www.mater-rep.com/EN/10.11896/cldb.21050254 OR http://www.mater-rep.com/EN/Y2022/V36/I23/21050254

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