碳纤维/玄武岩纤维混合层合板的弹道性能和冲击后压缩行为

张龙飞; 林高建; 袁野; 周志鹏

doi:10.11858/gywlxb.20251073

碳纤维/玄武岩纤维混合层合板的弹道性能和冲击后压缩行为

doi: 10.11858/gywlxb.20251073

张龙飞^1,,
林高建^1,*, ,,
袁野^{1, 2},
周志鹏³

1.
北京理工大学爆炸科学与安全防护全国重点实验室, 北京　100081
2.
北京理工大学重庆创新中心, 重庆　401120
3.
山西警察学院, 山西太原　030401

基金项目: 国家重点研发计划（2023YFB4202902）；航空航天结构力学与控制全国重点实验室开放基金（MCAS-E-0124Y03）

详细信息

作者简介:
张龙飞（2000－），男，硕士研究生，主要从事复合材料冲击与防护研究. E-mail：1299920372@qq.com

通讯作者:
林高建（1992－），男，博士，工程师，主要从事复合材料研究. E-mail：394954032@qq.com

中图分类号: O347.3; O521.9; TB33
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- 文章访问数: 662
- HTML全文浏览量: 256
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出版历程
- 收稿日期: 2025-04-09
- 修回日期: 2025-05-07
- 网络出版日期: 2025-05-12
- 刊出日期: 2026-02-05

Ballistic and Compression after Impact Behaviors of Carbon/Basalt Fiber Hybrid Laminate

ZHANG Longfei^1
,,
LIN Gaojian^{1,*
, ,},
YUAN Ye^{1, 2},
ZHOU Zhipeng³

1.
State Key Laboratory of Explosion Science and Safety Protection, Beijing Institute of Technology, Beijing 100081, China
2.
Beijing Institute of Technology Chongqing Innovation Center, Chongqing 401120, China
3.
Shanxi Police College, Taiyuan 030401, Shanxi, China

摘要

摘要: 探究了不同碳纤维/玄武岩纤维（carbon fiber/basalt fiber，CF/BF）配比的混杂层合板在弹道冲击及冲击后压缩（compression after impact，CAI）性能方面的表现，结果表明，玄武岩纤维显著提升了混杂层合板的能量吸收能力。采用C扫描、电子显微镜和扫描电镜分析了材料的损伤机制，揭示了材料性能提升的内在机理。另一方面，混杂层合板的初始压缩强度随玄武岩纤维含量的增加而下降。在混杂层合板的能量吸收能力增强与初始压缩强度下降的共同作用下，CAI测试中受损层合板的残余压缩强度呈局部波动趋势。研究结果可为轻量化、高抗冲击复合材料的结构设计提供指导。
- 高速冲击 /
- 失效机制 /
- 冲击后压缩 /
- 层合板
Abstract: This study examines the ballistic and compression after impact (CAI) performance of carbon fiber/basalt fiber (CF/BF) hybrid laminates with different CF/BF ratios. C-scanning, electron microscopy, and scanning electron microscope were used to investigate the damage mechanisms, providing insights into the mechanism of the improved performance. The results show that the basalt fiber significantly enhances the energy absorption capacity of the hybrid laminates. Although the compression strength of the original hybrid laminates monotonically decreases with the increasing BF content ratio, the residual compression strength measured from CAI tests shows a locally wavy trend due to the competition between the increased energy absorption capacity and decreased original compression strength. This study offers guidance for designing lightweight, impact-resistant composite structures.
- high-velocity impact /
- failure mechanism /
- post-impact compression /
- composite structures

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图 1 层合板制备过程

Figure 1. Preparation process of laminate

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图 2 不同纤维预浸料组成的 24 层复合材料层合板试样构型示意图

Figure 2. Schematic diagram of laminated configurations with 24 layers of varying fiber prepregs

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图 3 弹道枪测试系统的实验装置示意图

Figure 3. Experimental setup of the ballistic gun testing system

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图 4 (a) 层合板夹具，(b)层合板夹具示意图，(c) CAI 测试实验装置

Figure 4. (a) Laminate fixture; (b) schematic diagram of laminate fixture; (c) experimental setup for the CAI tests

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图 5 CFRP层合板的侵彻实验结果

Figure 5. Penetration experimental results of CFRP laminates

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图 6 球形弹丸穿透过程

Figure 6. Perforation process of spherical projectile

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图 7 层合板经弹道冲击实验后的背面细节：(a) CF、(b) (C3B1)₆、(c) (C1B1)₁₂、(d) (C1B3)₆和 (e) BF

Figure 7. Details of the back faces of the laminates after ballistic impact testing for (a) CF, (b) (C3B1)₆, (c) (C1B1)₁₂, (d) (C1B3)₆, and (e) BF

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8 冲击后区域的分层区域 C 扫描结果：(a) CF，(b) (C3B1)₆，(c) (C1B1)₁₂，(d) (C1B3)₆，(e) BF

8. C-scan results of the impact region showing the delamination region tested by C-scan after the impact tests: (a) CF, (b) (C3B1)₆, (c) (C1B1)₁₂, (d) (C1B3)₆, (e) BF

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图 9 不同层合板抗冲击结果：(a) δ_EAR，(b) δ_SEA，(c) 内部分层区域，(d) 速度差

Figure 9. Impact test results of different laminates: (a) δ_EAR, (b) δ_SEA, (c) internal delamination, (d) difference of penetration velocity

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图 10 冲击后断口损伤形貌 SEM 图像： (a) CF，(b) (C1B1)₁₂

Figure 10. SEM images of damage after impact testing: (a) CF, (b) (C1B1)₁₂

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图 11 (a)不同层合板冲击后的位移-载荷曲线，(b) 不同层合板冲击后的压缩破坏载荷、分层面积以及δ_SEA变化曲线

Figure 11. (a) Displacement-load curves of different laminates after impact; (b) compression fracture load, delamination area, and SEA variation curves of different laminates after impact

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图 12 (C1B1)₁₂样品冲击后压缩引起的膨胀^[55]

Figure 12. Compression-induced bulging of (C1B1)₁₂ after impact^[55]

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图 13 (a) 压缩过程中裂纹扩展示意图，(b) 电子显微镜图像

Figure 13. (a) Schematic diagram of crack extension during compression; (b) electron microscope images

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表 1 不同层合板的冲击实验结果

Table 1. Impact experimental results of different laminates

Specimen	Initial velocity/(m·s^–1)	Residual velocity/(m·s^–1)	Velocity difference/(m·s^–1)	Energy absorption/J
CF	213.74	176.77	36.97	66.27
CF	234.11	200.57	33.54	66.92
(C3B1)₆	231.40	193.64	37.76	73.67
(C3B1)₆	242.21	196.08	46.13	92.80
(C1B1)₁₂	225.44	174.56	50.88	93.42
(C1B1)₁₂	225.81	177.66	48.15	89.17
(C1B3)₆	234.90	155.56	79.34	142.19
(C1B3)₆	237.69	155.38	82.31	148.50
BF	238.50	136.72	101.78	175.29
BF	236.09	142.71	93.38	162.36

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