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

ZHOU Zhixuan; WANG Mafa; LI Junling; MA Zhaoxia

doi:10.11883/bzycj-2021-0251

Volume 42 Issue 8

Sep. 2022

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ZHOU Zhixuan, WANG Mafa, LI Junling, MA Zhaoxia. Crater characteristics of carbon fiber/epoxy composite under hypervelocity impact in the velocity range from 3.0 km/s to 6.5 km/s[J]. Explosion And Shock Waves, 2022, 42(8): 083301. doi: 10.11883/bzycj-2021-0251

Citation:

ZHOU Zhixuan, WANG Mafa, LI Junling, MA Zhaoxia. Crater characteristics of carbon fiber/epoxy composite under hypervelocity impact in the velocity range from 3.0 km/s to 6.5 km/s[J]. Explosion And Shock Waves, 2022, 42(8): 083301. doi: 10.11883/bzycj-2021-0251

Citation:

ZHOU Zhixuan, WANG Mafa, LI Junling, MA Zhaoxia. Crater characteristics of carbon fiber/epoxy composite under hypervelocity impact in the velocity range from 3.0 km/s to 6.5 km/s[J]. Explosion And Shock Waves, 2022, 42(8): 083301. doi: 10.11883/bzycj-2021-0251

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

doi: 10.11883/bzycj-2021-0251

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

Received Date: 2021-06-28
Rev Recd Date: 2022-03-14

Available Online: 2022-03-30

Publish Date: 2022-09-09

Abstract

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

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References(15)

References

[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.