热塑性纤维金属层合板舱内爆炸响应数值模拟

周沪; 孔祥韶; 刘芳; 郑成

doi:10.11858/gywlxb.20210821

热塑性纤维金属层合板舱内爆炸响应数值模拟

doi: 10.11858/gywlxb.20210821

周沪^1,,
孔祥韶¹,
刘芳^2,*, ,,
郑成¹

1.
武汉理工大学绿色智能江海直达船舶与邮轮游艇研究中心，湖北武汉　430063
2.
武汉理工大学交通与物流工程学院，湖北武汉　430063

基金项目: 装备预先研究教育部联合基金青年人才项目（6141A02033108）

详细信息

作者简介:
周　沪（1994－），男，博士，主要从事结构动力学研究. E-mail：zhouhu@whut.edu.cn

通讯作者:
刘　芳（1984－），女，博士，副教授，主要从事材料弹塑性损伤本构关系、结构弹塑性损伤力学响应研究. E-mail：fang_liu@whut.edu.cn

中图分类号: O347.3
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出版历程
- 收稿日期: 2021-06-18
- 修回日期: 2021-09-04
- 录用日期: 2021-11-25

Numerical Analysis of Response of Fiber Reinforced Thermoplastic and Metal Laminates Subjected to Explosion in Cabin

ZHOU Hu^1
,,
KONG Xiangshao¹,
LIU Fang^{2,*
, ,},
ZHENG Cheng¹

1.
Green and Smart River-Sea-Going Ship, Cruise and Yacht Research Center, Wuhan University of Technology, Wuhan 430063, Hubei, China
2.
School of Transportation and Logistics Engineering, Wuhan University of Technology, Wuhan 430063, Hubei, China

摘要

摘要: 热塑性纤维金属层合板作为具备优良抗冲击潜能的复合材料，在舰船防护领域受到广泛关注。以热塑性纤维金属层合板为研究对象，基于封闭空间内爆炸载荷作用下层合板动态响应试验数据，以及通过代表体积元（representative volume element, RVE）方法计算得到的纤维板材料参数，开展了热塑性纤维增强金属层合板的数值模拟研究。通过试验结果与数值模拟结果的对比，验证了数值模拟方法的有效性，进一步分析了层合板的响应规律。所采用的热塑性纤维金属层合板舱内爆炸响应数值模拟方法对研究层合板抗冲击性能具有一定的借鉴意义，为相关研究的进一步开展提供了思路。
- 纤维金属层合板 /
- 舱内爆炸 /
- 抗冲击性能
Abstract: Fiber reinforced thermoplastic and metal laminates have received wide attention in the field of naval protection, due to the excellent impact resistance performance. Numerical study on the fiber reinforced thermoplastic and metal laminate was carried out, based on the dynamic response test data of the laminate subjected to blast load in a confined space and the mechanical performance parameters of fiber reinforced thermoplastic calculated by the representative volume element (RVE) method. The validity of the numerical method was verified by comparing the test results with simulation one, and the response law of the laminate was further analyzed by the simulation results. The numerical simulation method of the fiber-reinforced thermoplastic and metal laminates adopted in this paper has a certain significance for the study of the impact resistance of laminates, and provides a feasible idea for the further development of related research.
- fiber reinforced thermoplastic and metal laminate /
- explosion in the cabin /
- impact resistance

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图 1 热塑性纤维增强金属层合板铺层形式

Figure 1. Lay-up of fiber reinforced thermoplastic and metal laminate

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图 2 封闭箱体示意图

Figure 2. Schematic diagram of enclosed cabin

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图 3 试验过程中整体装置架设

Figure 3. Set-up of the tests

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图 4 截面典型破坏模式

Figure 4. Typical damage mode (sectional view)

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图 5 编织纤维布在不同尺度的构成关系

Figure 5. Structure of fiber reinforced thermoplastic metal laminates

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图 6 纤维布编织方法

Figure 6. Fiber of weaving method

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图 7 玻璃纤维截面

Figure 7. Cross section of glass fiber

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图 8 纤维束截面

Figure 8. Cross section of fiber yarn

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图 9 代表体积元模型

Figure 9. Representative volume element model

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图 10 二维载荷计算模型

Figure 10. Two-dimensional load calculation model

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图 11 二维起爆压力云图

Figure 11. Two-dimensional detonation pressure fringe

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图 12 整体模型设置

Figure 12. Overall model settings

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图 13 层合板部位模型剖视图

Figure 13. Sectional view of laminate model

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图 14 铝合金拉伸应力-应变曲线

Figure 14. Stress-strain curve of aluminum alloy

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图 15 夹持部分边界条件施加

Figure 15. Boundary conditions of the clamping part

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图 16 铝板与纤维板间的绑定

Figure 16. Bonding between the aluminum plate and laminate

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图 17 试验与数值模拟最终变形的对比

Figure 17. Comparison of final deformation between test and simulation

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图 18 面板变形模式

Figure 18. Deformation mode of the laminate

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图 19 固支边界范围

Figure 19. Range of fixed boundary

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图 20 纤维板损伤模式对比

Figure 20. Damage mode of laminate

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图 21 层合板截面变形与分层

Figure 21. Deformation and delamination of laminate (sectional view)

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图 22 典型层合板响应过程

Figure 22. Typical laminate response process

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表 1 试验工况

Table 1. Test conditions

Specimen No.	m/g	d/mm	W/g	D/mm	h/mm
A5G4-1	1 108	6.5	5	15.0	17.8
A5G4-2	1 108	6.5	10	20.0	20.0
A5G4-3	1 108	6.5	20	25.0	25.6
A5G4-4	1 108	6.5	30	30.0	26.7
A5G4-5	1 108	6.5	40	30.0	35.6
A5G4-6	1 108	6.5	50	35.0	32.7

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表 2 层合板试验变形数据

Table 2. Deformation of the laminate

Specimen No.	d/mm	W/g	δ_max/mm
A5G4-1	6.5	5	9.3
A5G4-2	6.5	10	13.5
A5G4-3	6.5	20	18.9
A5G4-4	6.5	30	26.2
A5G4-5	6.5	40	32.8
A5G4-6	6.5	50	39.7

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表 3 药量递增下截面破坏形式变化

Table 3. Damage mode under different charge (sectional view)

Specimen No.	Cross-sectional scan image	Deformation characteristics
A5G4-2		Slight delamination occurred
A5G4-3		Initial damage began
A5G4-4		Fiber layers broken and failed, obvious delamination at the center and the boundary
A5G4-5		All fiber layers broken, delamination appears on each metal-fiber interface
A5G4-6		Metal layers has obvious protrusions and delamination

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表 4 复合材料内部纤维的几何参数

Table 4. Fiber geometrical parameters of the laminate

Weaving form	Fiber diameter/μm	Fiber bundle density/tex	Long axis of fiber section/μm	Short axis of fiber section/μm
1/7 satin	6.0	68	110	500

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表 5 复合材料的组成及其力学性能参数

Table 5. Composition of the laminate and their mechanical parameters

Material	$\rho$_f/(g∙cm⁻³)	E/GPa	μ	w/%
E-glass fiber	2.45	71.00	0.2	60
PP	0.91	0.89	0.4	40

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表 6 复合材料性能参数

Table 6. Mechanical parameters of the laminate

E₁₁/GPa	E₂₂/GPa	E₃₃/GPa	G₁₂/GPa	G₁₃/GPa	G₂₃/GPa	μ₁₂	μ₁₃	μ₃₂
13.60	13.60	3.12	0.78	0.82	0.82	0.05	0.54	0.12

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表 7 二维载荷计算中的TNT参数

Table 7. TNT parameters for two-dimensional load calculation model

CJ detonation parameters				JWL state equation parameters
$\,\rho$_C/(g∙cm⁻³)	D_C-J/(m∙s⁻¹)	p_C-J/GPa	E_C/(MJ∙m⁻³)	A/GPa	B/GPa	R₁	R₂	$\omega $
1.55	6 487	18.39	5 235	373.77	3.75	4.15	0.90	0.35

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表 8 铝合金真实应力-应变输入参数

Table 8. True stress-strain parameters of aluminum alloys

Plastic strain/%	Stress/MPa	Plastic strain/%	Stress/MPa	Plastic strain/%	Stress/MPa
0	110.93	4.137	182.47	12.767	241.73
0.003	111.12	5.028	192.73	13.778	245.02
0.188	116.92	5.846	200.54	15.196	250.26
0.546	124.20	6.727	209.26	16.371	253.58
0.958	133.40	7.505	214.37	18.246	258.65
1.506	143.87	8.356	220.41	18.662	259.99
2.058	154.52	10.237	230.85
3.090	169.07	11.604	236.80

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表 9 纤维板材料参数

Table 9. Mechanical parameters of fiber reinforced laminate

Equation of state						Strength equation
E₁₁/GPa	E₂₂/GPa	E₃₃/GPa	μ₁₂	μ₂₃	μ₃₁	G/MPa
13.6	13.6	3.12	0.05	0.54	0.12	820

Failure criterion						Post-failure mode
σ₁₁/MPa	σ₂₂/MPa	σ₃₃/MPa	τ₁₂/MPa	τ₂₃/MPa	τ₃₁/MPa	Residual shear stiffness
550	550	550	220	220	220	0.2

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Directional failure mode
11	22	33	12	23	31
11 only	22 only	33 only	12 and 11 only	23 and 11 only	31 and 11 only

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表 10 夹持边界与固支边界对比

Table 10. Comparison of clamping and fixed boundary

Final deformation/mm	Final deformation of the clamping boundary/mm	Final deformation of the fixed boundary/mm	Boundary influence/%
13.5	12.8	9.2	28.1

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