Modeling and Analysis of Thermo-Mechanical Behavior for Fiber Fabric under Hypervelocity Impact

被引：0

作者：

Zhang Y. ^{[1
]}

Wang Y.-L. ^{[2
]}

Shi J.-F. ^{[1
]}

Yu D. ^{[3
]}

Xu H.-D. ^{[1
]}

Ma F.-J. ^{[4
]}

Song D. ^{[5
]}

Miao C.-Q. ^{[1
]}

机构：

[1] National Key Laboratory of Science and Technology on Advanced Composites in Special Environments, Harbin Institute of Technology, Harbin

[2] Department of Aerospace Research and Exploration, China Academy of Launch Vehicle Technology, Beijing

[3] Department of Mechanical Design, School of Mechanical and Electrical Engineering, Harbin Institute of Technology, Harbin

[4] China Aerodynamics Research and Development Center, Mianyang

[5] School of Mechanical and Electrical Engineering, University of Electronic Science and Technology of China, Chengdu

来源：

Yuhang Xuebao/Journal of Astronautics | 2021年 / 42卷 / 11期

关键词：

Fiber fabric; Hypervelocity impact; Johnson-Cook model; Orbital debris shielding; Unit-cell model;

D O I：

10.3873/j.issn.1000-1328.2021.11.014

中图分类号：

学科分类号：

摘要：

A new thermo-mechanical model for fiber fabric of hypervelocity impact is established by using the Johnson-Cook model, the Gruneisen equation of state and the FEM-SPH coupling algorithm, while some new factors are taken into account such as the heat generation, strain rate strengthening and high temperature softening of materials. Mechanical and thermal information could be obtained with the model, such as penetration, fragmentation, stress and strain, heat generation and temperature field of fiber fabric. The analysis results are in good agreement with the experimental results. © 2021, Editorial Dept. of JA. All right reserved.

引用

页码：1475 / 1482

页数：7

共 35 条

[1] Sockalingam S, Chowdhury S C, Gillespie J W, Et al., Recent advances in modeling and experiments of Kevlar ballistic fibrils, fibers, yarns and flexible woven textile fabrics-a review, Textile Research Journal, 87, 8, pp. 984-1010, (2017)
[2] Christiansen E L, Crews J L, Williamsen J E, Et al., Enhanced meteoroid and orbital debris shielding, International Journal of Impact Engineering, 17, 1-3, pp. 217-228, (1995)
[3] Christiansen E L, Kerr J H, De la Fuente H M, Et al., Flexible and deployable meteoroid/debris shielding for spacecraft, International Journal of Impact Engineering, 23, 1, pp. 125-136, (1999)
[4] Guan Gong-shun, Feng Shuo, Pang Bao-jun, Et al., Damage and ballistic limit for three-layer aluminum plate structure under high-velocity impact, Journal of Astronautics, 37, 3, (2016)
[5] Seedhouse E., Bigelow aerospace colonizing space one module at a time, (2015)
[6] Liu Bin-tao, Jia Guang-hui, Huang Hai, Numerical modeling and parameter identification for Kevlar laminate under the condition of hypervelocity impact, Journal of Astronautics, 32, 2, pp. 261-266, (2011)
[7] Singh T J, Samanta S., Characterization of Kevlarfiber and its composites: A review, Materials Today: Proceedings, 2, 4-5, pp. 1381-1387, (2015)
[8] Miao Chang-qing, Du Ming-jun, Huang Lei, Et al., Exper-imental research on hypervelocity impact characteristics of flexible anti-debris multi-shields structure, Manned Spaceflight, 23, 2, pp. 173-176, (2017)
[9] Tang En-ling, Xu Ming-yang, Zhang Qing-Ming, Et al., Study on partitioning of energy in hypervelocity impact on thick target, Chinese Journal of Solid Mechanics, 37, 2, pp. 152-160, (2016)
[10] Li Yi-xiao, Wang Sheng-jie, Material phase evolution in hypervelocity impact process, Chinese Journal of High Pressure Physics, 33, 6, pp. 75-83, (2019)

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