典型爆炸冲击载荷下T800碳纤维层合板的损伤特性

李天宇; 冯晓伟; 刘瑶璐; 何丽灵; 赵浩川; 王守乾; 聂源

doi:10.11883/bzycj-2024-0505

典型爆炸冲击载荷下T800碳纤维层合板的损伤特性

doi: 10.11883/bzycj-2024-0505

李天宇^1,,
冯晓伟^{1, 2, ,},
刘瑶璐³,
何丽灵^{1, 2},
赵浩川¹,
王守乾¹,
聂源¹

1.
中国工程物理研究院总体工程研究所, 四川绵阳 621999
2.
工程材料与结构冲击振动四川省重点试验室, 四川绵阳 621010
3.
重庆大学航空航天学院, 重庆 400044

基金项目: 中物院院长基金（YZJJZQ2024007）；国家自然科学基金（12102413）

详细信息

作者简介:
李天宇（1999－　），男，博士研究生，litianyu23@gscaep.ac.cn

通讯作者:
冯晓伟（1984－　），男，博士，副研究员，414fengxw@caep.cn

中图分类号: O347.3; V258
计量
- 文章访问数: 200
- HTML全文浏览量: 39
- PDF下载量: 60
- 被引次数: 0
出版历程
- 收稿日期: 2024-12-25
- 修回日期: 2025-10-14
- 网络出版日期: 2025-10-16

Damage characteristics of T800 CFRP laminates under typical impacts

1.
Institute of Systems Engineering, China Academy of Engineering Physics, Mianyang 621999, Sichuan, China
2.
Shock and Vibration of Engineering Materials and Structures Key Lab of Sichuan Province, Mianyang 621010, Sichuan, China
3.
College of Aerospace Engineering, Chongqing University, Chongqing 400044, China

摘要

摘要: 针对飞行器常用的碳纤维增强聚合物基复合材料层合板（carbon fiber-reinforced polymer，CFRP）抗冲击性能研究需求，对T800/3200 CFRP层合板进行球形破片侵彻试验与静爆试验，使用CT扫描技术与毁伤评估理论进行深入分析，研究了T800/3200 CFRP层合板在破片侵彻与爆炸冲击波2种典型载荷下的损伤特性与性能，并与航空制造业常用的2024-T3航空铝进行了试验对比。研究表明：T800/3200 CFRP层合板遭受球形破片侵彻后将产生近似台体的脱层失效区域，且失效区域的体积随着破片侵彻速度的增大而减小；T800/3200 CFRP层合板抵抗破片冲击载荷的能力不及航空铝板，吸收动能的能力约为航空铝板的一半；但其抗爆性能显著优于航空铝，在航行任务中更有助于保证飞行器的安全。
- T800碳纤维增强复合材料层合板 /
- 2024-T3航空铝 /
- 破片侵彻 /
- 爆炸冲击波 /
- 损伤模式
Abstract: In response to the research demand for the impact resistance of carbon fiber-reinforced polymer (CFRP) laminates commonly used in aircraft, spherical fragment penetration and static blast tests were conducted on T800/3200 CFRP laminates, with CT scanning technology and damage assessment theories employed for further analysis. The damage characteristics and performance of T800/3200 CFRP laminates under two typical loads-fragment penetration and explosive shock waves-were investigated and compared with 2024-T3 aluminum, a material widely used in the aviation manufacturing industry. Two control groups were established: tungsten fragments impacting aerospace aluminum plates and tungsten steel fragments striking CFRP laminates. Impact velocities and residual velocities were precisely measured using high-speed photography. During fragment penetration tests, relationships among incident velocity, residual velocity, and energy absorption were analyzed based on the Recht–Ipson ballistic limit model. The internal damage morphology of CFRP targets was examined in detail using high-resolution CT scanning technology to characterize delamination patterns and progressive failure across different depths and plies. In blast tests, the damage morphology and maximum deflection of target plates were systematically observed and recorded. The blast resistance of CFRP laminates and aluminum plates was quantitatively compared using advanced mathematical methods incorporating boundary condition equivalence and overpressure equivalence principles to ensure a fair and accurate comparison. The results show that, after spherical fragment penetration, the T800/3200 CFRP laminate generates a delamination damage zone resembling a truncated cone, with the volume of the cone decreasing as the penetration velocity of fragments increases. The T800/3200 CFRP laminate exhibits inferior performance against fragment penetration compared with aerospace aluminum but offers significantly enhanced blast resistance. This characteristic makes it more effective in maintaining structural safety and aerodynamic stability during flight missions under explosive threats. The findings provide theoretical and empirical support for improving the safety and reliability of aerospace vehicles through optimized material selection and structural design.
- T800 carbon fiber reinforced composite laminate /
- 2024-T3 aerospace aluminum /
- fragment penetration /
- explosive shock wave /
- damage modes

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图 1 破片载荷试验装置与场景

Figure 1. Penetration experiment scenario

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图 2 入射速度与剩余速度试验数据及拟合曲线

Figure 2. Incident and residual velocity data with fitting curves

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图 3 入射速度与动能损失关系

Figure 3. Relationship between incident velocity and energy loss

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图 4 入射速度与动能损失比例关系

Figure 4. Relationship between incident velocity and energy loss ratio

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图 5 各速度入射T800层合板破片致靶板各深度失效比率

Figure 5. Relationship between depth of CFRP plate and damage ratio

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图 6 各材质破片入射T800层合板破片致靶板各深度平均失效比率

Figure 6. Relationship between depth of CFRP plate and average damage ratio

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图 7 各速度入射破片致T800 CFRP靶板失效体积比率

Figure 7. Relationship between incident velocity and damage volume ratio of T800 CFRP plate

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图 8 冲击波载荷试验装置与场景

Figure 8. Shockwave load experiment scenario

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图 9 冲击波载荷试验各靶板处超压曲线

Figure 9. Overpressure curves in shockwave load experiment

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图 10 各靶板迎爆面形貌

Figure 10. Surface of each target plate upon impact

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图 11 参考试验平板宏观变形^[31]

Figure 11. Macroscopic deformation of reference experimental plates^[31]

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图 12 等效试验条件下2种靶板超压致挠信息

Figure 12. Deflection caused by overpressure on two types of target plates under equivalent experimental conditions

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表 1 T800/3200型CFRP靶板侵彻试验结果

Table 1. Fig.1 T800/3200 CFRP target plate penetration experimental results

试验编号	破片材质	靶体材质	入射速度/(m·s⁻¹)	剩余速度/(m·s⁻¹)
1	钨	T800/3200 CFRP	41	未穿透
2	钨	T800/3200 CFRP	178	16
3	钨	T800/3200 CFRP	183	86
4	钨	T800/3200 CFRP	190	126
5	钨	T800/3200 CFRP	227	172
6	钨	T800/3200 CFRP	149	未穿透
7	钨	T800/3200 CFRP	179	9
8	钨	T800/3200 CFRP	184	106
9	钨	T800/3200 CFRP	228	169
10	钨	T800/3200 CFRP	299	248
11	钨	T800/3200 CFRP	508	468
12	钨	2024-T3航空铝	243	4
13	钨	2024-T3航空铝	368	284
14	YG6钨钢	T800/3200 CFRP	182	103
15	YG6钨钢	T800/3200 CFRP	230	144

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表 2 层合板内部损伤CT扫描结果

Table 2. CT scan results of tested CFRP plates

试验编号	破片材质	入射速度/ (m·s⁻¹)	剩余速度/ (m·s⁻¹)	CT扫描形貌与深度/mm
3	7.08 g钨珠	183	86
3	7.08 g钨珠	183	86	0	1.01	2.23	2.84
5	7.08 g钨珠	227	172
5	7.08 g钨珠	227	172	0	0.5	1.52	2	2.4	3.5
7	7.08 g钨珠	179	9
7	7.08 g钨珠	179	9	0	0.6	1	1.51	2.2	2.7
8	7.08 g钨珠	184	106
8	7.08 g钨珠	184	106	0	0.42	0.86	1.27	1.71	2.13	2.37
10	7.08 g钨珠	299	248
10	7.08 g钨珠	299	248	0	0.6	1.2	1.8	2.5	3.2
11	7.08 g钨珠	508	468
11	7.08 g钨珠	508	468	0	1	1.6	2.5
14	5.25 g YG6钨钢	182	54
14	5.25 g YG6钨钢	182	54	0	0.5	1	1.5	2	2.5	3
15	5.25 g YG6钨钢	230	144
15	5.25 g YG6钨钢	230	144	0	0.5	1	1.5	2	2.5	3	3.5

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表 3 RI弹道极限模型拟合结果

Table 3. Fitting results using RI ballistic limit model

破片材质	靶体材质	拟合弹道极限速度/ (m·s⁻¹)
钨	T800/3200 CFRP	170
钨	铝	243
YG6钨钢	T800/3200 CFRP	174

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表 4 各次试验破片动能损失

Table 4. Fragment kinetic energy loss for each experiment

试验编号	弹体材质	靶板材质	初速度/(m·s⁻¹)	剩余速度/(m·s⁻¹)	初动能/J	剩余动能/J	动能损失/J
1	钨	T800/3200 CFRP	41	未穿透	5.95
2	钨	T800/3200 CFRP	178	16	112.16	0.91	111.26
3	钨	T800/3200 CFRP	183	86	118.55	26.18	92.37
4	钨	T800/3200 CFRP	190	126	127.79	56.20	71.59
5	钨	T800/3200 CFRP	227	172	182.41	104.73	77.69
6	钨	T800/3200 CFRP	149	未穿透	78.59
7	钨	T800/3200 CFRP	179	9	113.43	0.29	113.14
8	钨	T800/3200 CFRP	184	106	119.85	39.78	80.07
9	钨	T800/3200 CFRP	228	169	184.02	101.11	82.92
10	钨	T800/3200 CFRP	299	248	316.03	217.42	98.62
11	钨	T800/3200 CFRP	508	468	914.84	776.44	138.40
12	钨	2024-T3航空铝	243	4	208.74	0.06	208.68
13	钨	2024-T3航空铝	368	284	479.40	285.52	193.88
14	YG6	T800/3200 CFRP	182	54	86.95	7.65	79.30
15	YG6	T800/3200 CFRP	230	144	138.86	54.43	84.43

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表 5 层合板内部损伤CT扫描后处理结果

Table 5. Post-process of CT scan results of tested CFRP plates

试验编号	破片材质	入射速度/(m·s⁻¹)	剩余速度/(m·s⁻¹)	CT扫描形貌与深度/mm
3	7.08 g钨珠	183	86	不可用
3	7.08 g钨珠	183	86	0	1.01	2.23	2.84
5	7.08 g钨珠	227	172
5	7.08 g钨珠	227	172	0	0.5	1.52	2	2.4	3.5
7	7.08 g钨珠	179	9
7	7.08 g钨珠	179	9	0	0.6	1	1.51	2.2	2.7
8	7.08 g钨珠	184	106
8	7.08 g钨珠	184	106	0	0.42	0.86	1.27	1.71	2.13	2.37
10	7.08 g钨珠	299	248
10	7.08 g钨珠	299	248	0	0.6	1.2	1.8	2.5	3.2
11	7.08 g钨珠	508	468
11	7.08 g钨珠	508	468	0	1	1.6	2.5
14	5.25 g YG6钨钢	182	54	不可用					不可用
14	5.25 g YG6钨钢	182	54	0	0.5	1	1.5	2	2.5	3
15	5.25 g YG6钨钢	230	144								不可用
15	5.25 g YG6钨钢	230	144	0	0.5	1	1.5	2	2.5	3	3.5

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表 6 T800/3200型CFRP靶板冲击波载荷试验结果

Table 6. Test results in shockwave loading experiment of T800/3200 CFRP plate

试验编号	距离/m	峰值超压/kPa	冲量/（kPa·ms）
1	0.54	2231.29	21.51
2	1.00	890.84	126.67
3	1.46	268.87	73.64

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表 7 CFRP靶板受冲击波载荷形貌

Table 7. Morphology of tested CFRP plates under shock wave loads

试验编号	距离/m	最大挠度/mm	正面	反面	断裂形貌	脱层情况
1	0.54	7.3
2	1.00	3.0
3	1.46	2.7

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表 8 参考试验^[31]设置与测量结果

Table 8. Setup and results of reference experiment^[31]

参考试验编号	装药量/g	爆距/mm	最大挠度/mm
A1	60	175	完全破坏
A2	60	175	64.61
A3	60	240	48.24
A4	60	175	63.58
A5	60	300	45.45
B1	80	175	73.74
B2	80	240	56.87
B3	80	175	完全破坏
B4	80	300	43.69
B5	80	300	35.09

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表 9 参考试验超压与等效后挠度

Table 9. Overpressure and equivalent deflection of reference experiment

参考试验编号	装药量/g	爆距/mm	对比距离/ (m·kg^−1/3)	理论超压/MPa	最大挠度/mm	等效最大挠度/mm
A1	60	175	0.44701	3.53758	完全破坏
A2	60	175	0.44701	3.53758	64.61	158.40
A3	60	240	0.61305	1.81211	48.24	118.27
A4	60	175	0.44701	3.53758	63.58	155.88
A5	60	300	0.76631	1.20206	45.45	111.43
B1	80	175	0.40614	4.42033	73.74	180.79
B2	80	240	0.55699	2.19613	56.87	139.43
B3	80	175	0.40614	4.42033	完全破坏
B4	80	300	0.69624	1.42507	43.69	107.11
B5	80	300	0.69624	1.42507	35.09	86.03

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