碳纤维/环氧树脂复合材料3.0～6.5 km/s超高速撞击成坑特性研究

周智炫; 王马法; 李俊玲; 马兆侠

doi:10.11883/bzycj-2021-0251

碳纤维/环氧树脂复合材料3.0～6.5 km/s超高速撞击成坑特性研究

doi: 10.11883/bzycj-2021-0251

中国空气动力研究与发展中心超高速空气动力研究所，四川绵阳 621000

基金项目: 国家自然科学基金（11802330）

详细信息

作者简介:
周智炫（1979－），男，硕士，副研究员, yige-zzxuan@163.com

通讯作者:
王马法（1986－），男，博士，高级工程师, fujianwmf@163.com

中图分类号: O385
计量
- 文章访问数: 566
- HTML全文浏览量: 186
- PDF下载量: 122
- 被引次数: 0
出版历程
- 收稿日期: 2021-06-28
- 修回日期: 2022-03-14
- 网络出版日期: 2022-03-30
- 刊出日期: 2022-09-09

Crater characteristics of carbon fiber/epoxy composite under hypervelocity impact in the velocity range from 3.0 km/s to 6.5 km/s

Hypervelocity Aerodynamics Institute, China Aerodynamics Research and Development Center, Mianyang 621000, Sichuan, China

摘要

摘要: 为研究碳纤维/环氧树脂复合材料在超高速撞击下的成坑特性，利用二级轻气炮开展了直径为1.00~3.05 mm的铝球以3.0~6.5 km/s的速度正撞击尺寸为100 mm×100 mm×20 mm的碳纤维/环氧树脂复合材料靶板的实验，获得了碳纤维/环氧复合材料靶板的成坑形貌特征，并测量了坑深、成坑表面积、表面损伤面积等尺寸。结合文献数据分析了靶板的无量纲成坑深度p/d_p、无量纲坑径系数D_h/d_p、表面损伤面积等效直径D_e等随撞击速度、撞击能量的变化规律。结果表明：碳纤维/环氧树脂复合材料的无量纲成坑深度p/d_p和无量纲坑径系数D_h/d_p均与撞击速度呈2/3次幂关系；表面损伤面积等效直径D_e与弹丸撞击能量E呈幂函数关系；成坑深度大于成坑半径。
- 超高速撞击 /
- 成坑特性 /
- 碳纤维/环氧树脂复合材料 /
- 空间碎片
Abstract: To study the crater’s characteristics of carbon fiber/epoxy composite targets at the impact velocity of 3.0－6.5 km/s, experiments of some composite targets impacted by spherical aluminum projectiles were carried out by applying a two-stage light gas gun in China Aerodynamics Research and Development Center. The targets were one kind of unidirectional braiding laminates made of carbon fiber and epoxy. The density of the targets was 1.5 g/cm³ and the size was 100 mm×100 mm×20 mm. The targets were clamped by two aluminum plates in experiments. One aluminum plate with the thickness of 2.5 mm was set 40 mm behind the targets to test fragments after the targets. The projectile diameter ranged from 1.00 mm to 3.05 mm. The damage feature of each target was obtained. A central crater surrounded with a shallow spalling region was observed in all recovered targets. Different from a semi-spherical crater, the central crater had a proximately quadrate edge, a semi-spherical bottom and a tough and rugged wall. The shallow spalling region was extremely irregular. The parameters of the crater and the shallow spalling region, such as the crater depth, the superficial area of the crater, the superficial area of the spalling region, were measured and analyzed. Moreover, the variations of the dimensionless crater depth p/d_p, the dimensionless equivalent crater diameter D_h/d_p and the equivalent diameter D_e of the spalling region with the impact velocity and energy were analyzed. Results show that the p/d_p depends on the density ratio ρ_p/ρ_t with a power of 1/2, and on the impact velocity v_i with a power of 2/3. The results are in good agreement with NASA’s hypervelocity experiments on reinforced carbon-carbon targets. The relationship of D_h/d_p with ρ_p/ρ_t and v_i is similar to that of p/d_p with ρ_p/ρ_t and v_i. D_e is a power function of impact kinetic energy. The crater-shape coefficient p/D_h is slightly greater than 0.5, which means the crater depth is larger than the crater radius.
- hypervelocity impact /
- crater characteristics /
- carbon fiber/epoxy composite /
- space debris

HTML全文

图 1 实验设备

Figure 1. Experimental facility

下载: 全尺寸图片幻灯片

图 2 靶板装置

Figure 2. Target configuration with a sample inside

下载: 全尺寸图片幻灯片

图 3 碳纤维/环氧树脂复合材料的超高速撞击损伤特征

Figure 3. Damage features of carbon fiber/epoxy composite under hypervelocity impact

下载: 全尺寸图片幻灯片

图 4 成坑区和损伤区划分

Figure 4. Definitions of crater area and damage area

下载: 全尺寸图片幻灯片

图 5 与Christiansen实验^[4-5]相比较的成坑深度

Figure 5. Crater depths in comparison with Christiansen experimental data^[4-5]

下载: 全尺寸图片幻灯片

图 6 坑径系数拟合曲线

Figure 6. Fitting curve of the crater-diameter coefficient

下载: 全尺寸图片幻灯片

图 7 表面损伤面积等效直径与弹丸撞击能的关系

Figure 7. Equivalent crater diameters of surface-damage area varyied with the impact energy of projectiles

下载: 全尺寸图片幻灯片

图 8 坑形系数p/D_h随v_i的变化

Figure 8. Variation of p/D_h with v_i

下载: 全尺寸图片幻灯片

图 9 2p/d_p和D_h/d_p随v_i的变化

Figure 9. Variations of 2p/d_p and D_h/d_p with v_i

下载: 全尺寸图片幻灯片

表 1 实验条件

Table 1. Experimental conditions

实验	弹丸材料	弹丸直径/mm	弹丸质量/g	靶板尺寸	撞击速度/(km·s⁻¹)	动能/J
A01	AL2A12	1.00	0.0015	100 mm×100 mm×20 mm	5.859	25.75
A02	AL2A12	2.00	0.0120	100 mm×100 mm×20 mm	3.094	57.44
A03	AL2A12	2.00	0.0118	100 mm×100 mm×20 mm	4.142	101.22
A04	AL2A12	2.00	0.0121	100 mm×100 mm×20 mm	5.004	151.49
A05	AL2A12	2.00	0.0121	100 mm×100 mm×20 mm	5.922	212.17
A06	AL2A12	2.00	0.0119	100 mm×100 mm×20 mm	6.479	249.77
A07	AL2A12	3.05	0.0422	100 mm×100 mm×20 mm	5.700	685.54

下载: 导出CSV

表 2 实验结果

Table 2. Experimental results

实验	损伤模式	p /mm	D_h /mm	A_e /mm²	D_e /mm
A01	成坑，表层起翘、剥落	2.39	7.58	73.83	9.70
A02	成坑，表层剥落	4.31	6.72	95.10	11.00
A03	成坑，表层剥落	4.40	8.09	151.27	13.88
A04	成坑，表层剥落	4.32	8.17	189.18	15.52
A05	成坑，表层剥落	6.49	10.80	209.93	16.35
A06	成坑，表层剥落	6.54	10.46	218.40	16.68
A07	成坑，表层分层、剥落，背部纤维布分层	9.53	13.08	219.94	16.73

下载: 导出CSV

参考文献(15)

[1]	HUMES D H. Hypervelocity impact tests on Space Shuttle Orbiter RCC thermal protection material [J]. Journal of Spacecraft and Rockets, 1978, 15(4): 250–251. DOI: 10.2514/3.28010.
[2]	CHRISTIANSEN E L. Investigation of hypervelocity impact damage to space station truss tubes [J]. International Journal of Impact Engineering, 1990, 10(1): 125–133. DOI: 10.1016/0734-743X(90)90053-X.
[3]	CHRISTIANSEN E L, ORTEGA J. Hypervelocity impact testing of shuttle orbiter thermal protection system tiles [C]//Space Programs and Technologies Conference. Huntsville, USA: AIAA, 1990. DOI: 10.2514/6.1990-3666.
[4]	CHRISTIANSEN E L, CURRY M D, KERR J H, et al. Evaluation of the impact resistance of reinforced carbon-carbon [C]//Proceedings of the Ninth International Conference on Composite Materials (ICCM-9). Madrid, Spain: Woodhead Publishing Limited, 1993: 498–507.
[5]	CHRISTIANSEN E L, FRIESEN L. Penetration equations for thermal protection materials [J]. International Journal of Impact Engineering, 1997, 20(1): 153–164. DOI: 10.1016/S0734-743X(97)87489-1.
[6]	TENNYSON R C, LAMONTAGNE C. Hypervelocity impact damage to composites [J]. Composites Part A:Applied Science and Manufacturing, 2000, 31(8): 785–794. DOI: 10.1016/S1359-835X(00)00029-4.
[7]	LAMONTAGE C G, MANUELPILLAI G N, TAYLOR E A, et al. Normal and oblique hypervelocity impacts on carbon fibre/peek composites [J]. International Journal of Impact Engineering, 1999, 23(1): 519–532. DOI: 10.1016/S0734-743X(99)00101-3.
[8]	LAMONTAGNE C G, MANUELPILLAI G N, KERR J H, et al. Projectile density, impact angle and energy effects on hypervelocity impact damage to carbon fibre/peek composites [J]. International Journal of Impact Engineering, 2001, 26(1): 381–398. DOI: 10.1016/S0734-743X(01)00110-5.
[9]	LAMBERT M, SCHÄFER F. Hypervelocity impacts on thermal protections: a review of the ESA work [C]//3rd European Workshop on Thermal Protection Systems. Netherlands: European Space Research and Technology Centre, 1998.
[10]	NUMATA D, OHTANI K, ANYOJI M, et al. HVI tests on CFRP laminates at low temperature [J]. International Journal of Impact Engineering, 2008, 35(12): 1695–1701. DOI: 10.1016/j.ijimpeng.2008.07.055.
[11]	XIE W H, MENG S H, DING L, et al. High velocity impact tests on high temperature carbon-carbon composites [J]. Composites Part B:Engineering, 2016, 98: 30–38. DOI: 10.1016/j.compositesb.2016.05.031.
[12]	谢爱民, 黄洁, 宋强, 等. 多序列激光阴影成像技术研究及应用 [J]. 实验流体力学, 2014, 28(4): 84–88. DOI: 10.11729/syltlxpz04. XIE A M, HUANG J, SONG Q, et al. Research and application of multi sequences laser shadowgraph technique [J]. Journal of Experiments in Fluid Mechanics, 2014, 28(4): 84–88. DOI: 10.11729/syltlxpz04.
[13]	宋强, 黄洁, 文雪忠, 等. 10ns级序列激光阴影成像仪在超高速瞬态测量中的应用 [C]//中国力学大会—2017暨庆祝中国力学学会成立60周年大会论文集. 北京: 中国力学学会, 2017: 718–723.
[14]	张庆明, 黄风雷. 超高速碰撞动力学引论 [M]. 北京: 科学出版社, 2000: 100–101.
[15]	经福谦. 超高速碰撞现象 [J]. 爆炸与冲击, 1990, 10(3): 279–288. JING F Q. Hypervelocity impact phenomena [J]. Explosion and Shock Waves, 1990, 10(3): 279–288.