PSI - Issue 52

Huadong Xu et al. / Procedia Structural Integrity 52 (2024) 52–62 Author name / Structural Integrity Procedia 00 (2019) 000 – 000 For S3~S8, the residual kinetic energy of fragments from projectile is calculated by Eq. (2), and the specific absorbed energy S is calculated by Eq. (3). The energy absorption capability of various targets obtained by the above evaluation method is shown in Fig. 8. 61 10

99.4

100

60 Specific energy absoption /J  m 2  kg -1 89.6 70 80 90

73.1

72.4

71.6

71.0

70.4

64.1

50

Aramid PE Quartz Basalt

Nextel Al Plate Carbon Al mesh --

Material

Fig. 8. Energy absorption performance of various targets. It can be seen from Fig. 8 that UHMWPE fabric has the best energy absorption capability, and the S is 99.4 J/(kg/m 2 ) , followed by aramid fabric. The worst energy absorption performance is Al plate, and the S is only 64.1 J/(kg/m 2 ) . The comparison results of energy absorption capability of various materials are: UHMWPE > Aramid > Quartz > Basalt > Nextel > Al mesh > Carbon fiber > Al plate. 4. Conclusions In this paper, the energy absorption of multiple fabrics under hypervelocity impact loading was investigated by experiments. The conclusions in this work are shown as follows: 1. An evaluation methodology of absorbed energy was proposed to analysis the energy absorption of multiple fabrics in HVI experiments, which based on the initial velocity of projectiles, penetrated layers in fabric targets, the depth and volume of the impact crater on witness plate. 2. The energy absorption capability of different types of fabrics were evaluated, and found that UHMWPE and Aramid fabric have the higher energy absorption capacity. Acknowledgements The present work is supported by the Advanced Research Project of Manned Spaceflight under Grant Nos. 040101, and Science Foundation of the National Key Laboratory of Science and Technology on Advanced Composites in Special Environments. References Buslov, E. P., I. S. Komarov, V. V. Selivanov, V. A. Titov, N. A. Tovarnova and V. A. Feldstein 2019. Protection of inflatable modules of orbital stations against impacts of particles of space debris. Acta Astronautica 163, 54-61. Cha, J.-H., Y. Kim, S. K. Sathish Kumar, C. Choi and C.-G. Kim 2020. Ultra-high-molecular-weight polyethylene as a hypervelocity impact shielding material for space structures. Acta Astronautica 168, 182-190. Erik Seedhouse, M. M. S. 2015. Bigelow Aerospace :Colonizing Space One Module at a Time, Springer International Publishing. Fa-wei, K., H. Jie, W. Xue-zhong, L. Xin, L. Jing, L. Qing and L. Sen 2018. Study on shield configuration stuffed with the integrated fabric layer and its bracing structure. International Journal of Impact Engineering 121, 191-202. Ke, F.-w., J. Huang, X.-z. Wen, Z.-x. Ma and S. Liu 2016. Test study on the performance of shielding configuration with stuffed layer under hypervelocity impact. Acta Astronautica 127, 553-560. Kim, Y., C. Choi, S. K. Sathish Kumar and C.-G. Kim 2017. Hypervelocity impact on flexible curable composites and pure fabric layer bumpers