嵌锁式CFRP方形蜂窝夹芯梁低速冲击响应及失效机理

王志鹏; 李海波; 韦冰峰; 李剑峰; 张威; 王强; 秦庆华

doi:10.11883/bzycj-2021-0525

嵌锁式CFRP方形蜂窝夹芯梁低速冲击响应及失效机理

doi: 10.11883/bzycj-2021-0525

王志鹏^{1, 2,},
李海波³,
韦冰峰³,
李剑峰^{1, 2},
张威^{1, 2},
王强^{1, 2},
秦庆华^{1, 2, 3, 4, ,}

1.
西安交通大学机械结构强度与振动国家重点实验室，陕西西安 710049
2.
西安交通大学航天航空学院极端环境与防护技术联合研究中心，陕西西安 710049
3.
北京强度环境研究所可靠性与环境工程技术重点实验室，北京 100076
4.
宁波大学冲击与安全工程教育部重点实验室，浙江宁波 315211

基金项目: 国家自然科学基金（11972281）；陕西省自然科学基金（2020JM-034）；航天一院高校联合创新基金（CALT201708）；宁波大学冲击与安全工程教育部重点实验室开放课题 (CJ202003）

详细信息

作者简介:
王志鹏（1993－　），男，博士研究生，zhipengwang@stu.xjtu.edu.cn

通讯作者:
秦庆华（1976－　），男，博士，教授，qhqin@mail.xjtu.edu.cn

中图分类号: O347.3
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- 被引次数: 0
出版历程
- 收稿日期: 2021-12-23
- 修回日期: 2022-05-18
- 网络出版日期: 2022-05-27
- 刊出日期: 2022-07-25

Low-velocity impact response and failure mechanism of CFRP sandwich beams with a square honeycomb core fabricated by the interlocking method

WANG Zhipeng^{1, 2
,},
LI Haibo³,
WEI Bingfeng³,
LI Jianfeng^{1, 2},
ZHANG Wei^{1, 2},
WANG Qiang^{1, 2},
QIN Qinghua^{1, 2, 3, 4
, ,}

1.
State Key Laboratory for Strength and Vibration of Mechanical Structures, Xi’an Jiaotong University, Xi’an 710049, Shaanxi China
2.
Joint Research Center for Extreme Environment and Protection Technology, School of Aerospace, Xi’an Jiaotong University, Xi’an 710049, Shaanxi, China
3.
Science and Technology on Reliability and Environment Engineering Laboratory, Beijing Institute of Structure and Environment Engineering, Beijing 100076, China
4.
Key Laboratory of Impact and Safety Engineering, Ministry of Education, Ningbo University, Ningbo 315211, Zhejiang, China

摘要

摘要: 采用嵌锁组装工艺制备了碳纤维/树脂基复合材料方形蜂窝夹芯梁，实验研究了低速冲击载荷下简支和固支夹芯梁的动态响应及失效机理，获得了不同冲击速度下夹芯梁的失效模式，分析了其损伤演化过程和失效机理，探讨了冲击速度、边界条件、面板质量分布以及槽口方向等因素对夹芯梁破坏模式及承载能力的影响。研究结果表明，芯材长肋板槽口方向对夹芯梁的失效模式有较大影响，槽口向上的芯材跨中部分产生了挤压变形，而槽口向下的芯材跨中部分槽口在拉伸作用下出现了沿槽口开裂失效，继而引起面板脱粘和肋板断裂；同等质量下，较厚的上面板设计可以提高夹芯梁的抗冲击能力，冲击速度越大，夹芯梁的峰值载荷和承载能力越高；固支边界使得夹芯梁的后失效行为呈现出明显的强化效应，在夹芯梁跨中部分发生初始失效后出现了后继的固支端芯材和面板断裂失效模式。
- 碳纤维/树脂基复合材料 /
- 方形蜂窝 /
- 嵌锁组装工艺 /
- 低速冲击
Abstract: Composite sandwich beams with a carbon fiber reinforced polymer (CFRP) square honeycomb core were designed and fabricated by using the interlocking method. The dynamic response and failure mechanism of fully-clamped and simply- supported sandwich beams subjected to low-velocity impact were investigated experimentally and the corresponding failure modes of the sandwich beams were obtained. Meanwhile, the damage evolvement process and the failure mechanism were analyzed in detail. Influences of the impact velocity, boundary conditions, the mass distributions of face sheets and the direction of the slots on the failure modes and load-carrying capacity of the sandwich beams were explored. The low-velocity impact experiments of composites specimens with two kinds of boundary conditions were carried out by using the drop-hammer impact test system. Three kinds of initial impact velocity were considered for the simply-supported and the fully- clamped sandwich beams sandwich beams, respectively. In the experiments, the time history curves of the impact load and the midspan deflection of the specimens were recorded by a load cell and a laser displacement sensor. Meanwhile, the deformation processes of the sandwich beams were captured by a high-speed camera. The experimental results show that the directions for the slots of the long ribs have significant influence on the failure modes of the sandwich beams. The sandwich core with the upward slots at the midspan has compression deformation whilst the cracking failure along the direction of the downward slots at the midspan is observed due to the tension, which results in the face-sheet debonding and rib fracture successively. It is found that for the same mass, the design of the thicker upper face sheet can enhance the impact resistance of the sandwich beams. The peak load and load-carrying capacity of the sandwich beams increase with increasing the impact velocity. The fully-clamped boundary conditions make the sandwich beams exhibit hardening post-failure behaviors obviously. After the initial failure at the midspan, the fully-clamped ends of the cores and the face-sheets of the sandwich beams experience the fracture failure.
- carbon fiber reinforced polymer composites /
- square honeycomb /
- interlocking method /
- low-velocity impact

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图 1 嵌锁式CFRP方形蜂窝夹芯梁制备过程和实物图

Figure 1. Fabrication process and images of CFRP sandwich beams with a square honeycomb core based on the interlocking method

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图 2 嵌锁式CFRP方形蜂窝夹芯梁低速冲击试样参数设计

Figure 2. Designs of CFRP sandwich beams with a square honeycomb subjected to low-velocity impact

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图 3 简支和固支CFRP蜂窝夹芯梁的低速冲击实验装置

Figure 3. Experimental setup of simply supported and fully clamped CFRP sandwich beams subjected to low-velocity impact

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图 4 CFRP方形蜂窝简支梁在低速冲击载荷作用下的力时程曲线和损伤演化过程

Figure 4. Impact load-time curves and corresponding failure processes of simply-supported CFRP sandwich beams subjected to low-velocity impact

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图 5 试样S-1.98-[1.6/16/0.8]的最终失效模式

Figure 5. The final failure modes of specimen S-1.98-[1.6/16/0.8]

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图 6 CFRP方形蜂窝简支梁在低速冲击载荷作用下的力时程曲线和损伤演化过程

Figure 6. Impact load-time curves and corresponding failure processes of simply-supported CFRP sandwich beams subjected to low-velocity impact

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图 7 试样S-2.80-[0.8/16/1.6]最终失效模式

Figure 7. Final failure modes of specimen S-2.80-[0.8/16/1.6]

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图 8 简支CFRP方形蜂窝夹芯梁在低速冲击载荷作用下的载荷挠度曲线

Figure 8. Impact load-deflection curves of simply-supported CFRP sandwich beams subjected to low-velocity impact

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图 9 CFRP方形蜂窝固支梁在低速冲击载荷作用下的力时程曲线和损伤演化过程

Figure 9. Impact load-time curves and corresponding failure process of fully clamped CFRP sandwich beams subjected to low-velocity impact

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图 10 试样C-3.43-[0.8/16/1.6]最终失效模式

Figure 10. Final failure mode of specimen C-3.43-[0.8/16/1.6]

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图 11 CFRP方形蜂窝固支梁在低速冲击载荷作用下的力时程曲线和损伤演化过程

Figure 11. Impact load-time curves and corresponding failure processes of fully-clamped CFRP sandwich beams subjected to low-velocity impact

下载: 全尺寸图片幻灯片

图 12 试样C-2.80-[0.8/16/1.6]的最终失效模式

Figure 12. Final failure modes of specimen C-2.80-[0.8/16/1.6]

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图 13 固支CFRP方形蜂窝夹芯梁在低速冲击载荷作用下的载荷挠度曲线

Figure 13. Impact load-deflection curves of fully clamped CFRP sandwich beams subjected to low-velocity impact

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表 1 CFRP方形蜂窝简支夹芯梁低速冲击实验设计

Table 1. Experimental design of simply-supported CFRP sandwich beams subjected to low-velocity impact

试样	上面板厚度/mm	芯材厚度/mm	下面板厚度/mm	冲击速度/(m·s⁻¹)	长肋板槽口方向
S-0.017×10⁻³-[1.2/16/1.2]^[7]	1.2	16	1.2	0.017×10⁻³	−Z
S-0.99-[0.8/16/1.6]	0.8	16	1.6	0.99	−Z
S-0.99-[1.2/16/1.2]	1.2	16	1.2	0.99	+Z
S-0.99-[1.6/16/0.8]	1.6	16	0.8	0.99	−Z
S-1.98-[0.8/16/1.6]	0.8	16	1.6	1.98	−Z
S-1.98-[1.2/16/1.2]	1.2	16	1.2	1.98	−Z
S-1.98-[1.6/16/0.8]	1.6	16	0.8	1.98	−Z
S-2.80-[0.8/16/1.6]	0.8	16	1.6	2.80	+Z
S-2.80-[1.2/16/1.2]	1.2	16	1.2	2.80	−Z
S-2.80-[1.6/16/0.8]	1.6	16	0.8	2.80	+Z

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表 2 CFRP方形蜂窝固支夹芯梁低速冲击实验设计

Table 2. Experimental design of fully-clamped CFRP sandwich beams subjected to low-velocity impact

试样	上面板厚度/mm	芯材厚度/mm	下面板厚度/mm	冲击速度/(m·s⁻¹)	长肋板槽口方向
C-2.80-[0.8/16/1.6]	0.8	16	1.6	2.80	+Z
C-2.80-[1.2/16/1.2]	1.2	16	1.2	2.80	+Z
C-2.80-[1.6/16/0.8]	1.6	16	0.8	2.80	−Z
C-3.43-[0.8/16/1.6]	0.8	16	1.6	3.43	−Z
C-3.43-[1.2/16/1.2]	1.2	16	1.2	3.43	−Z
C-3.43-[1.6/16/0.8]	1.6	16	0.8	3.43	−Z
C-3.96-[0.8/16/1.6]	0.8	16	1.6	3.96	−Z
C-3.96-[1.2/16/1.2]	1.2	16	1.2	3.96	−Z
C-3.96-[1.6/16/0.8]	1.6	16	0.8	3.96	−Z

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表 3 简支CFRP方形蜂窝夹芯梁峰值载荷

Table 3. The peak loads of simply supported CFRP sandwich beams subjected to low-velocity impact

试样	峰值载荷/kN
S-0.017×10⁻³-[1.2/16/1.2]	3.05
S-0.99-[0.8/16/1.6]	4.05
S-0.99-[1.6/16/0.8]	4.25
S-1.98-[0.8/16/1.6]	3.03
S-1.98-[1.2/16/1.2]	3.17
S-1.98-[1.6/16/0.8]	3.77
S-2.80-[0.8/16/1.6]	4.94
S-2.80-[1.2/16/1.2]	3.81
S-2.80-[1.6/16/0.8]	5.38

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表 4 固支CFRP方形蜂窝夹芯梁峰值载荷

Table 4. The peak loads of fully-clamped CFRP sandwich beams subjected to low-velocity impact

试样	峰值载荷/kN
C-2.80-[0.8/16/1.6]	7.39
C-2.80-[1.2/16/1.2]	7.24
C-2.80-[1.6/16/0.8]	6.65
C-3.43-[0.8/16/1.6]	8.91
C-3.43-[1.2/16/1.2]	10.62
C-3.43-[1.6/16/0.8]	11.80
C-3.96-[1.6/16/0.8]	10.43

下载: 导出CSV

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