爆炸载荷下舱内泡沫铝夹芯结构的动响应特性

谢悦; 侯海量; 李典

doi:10.11858/gywlxb.20210849

爆炸载荷下舱内泡沫铝夹芯结构的动响应特性

doi: 10.11858/gywlxb.20210849

海军工程大学舰船与海洋学院, 湖北武汉　430033

基金项目: 国家自然科学基金（51979277）

详细信息

作者简介:
谢　悦（1998－），女，硕士，主要从事舰船舱内爆炸结构防护研究. E-mail：Etsu0630@163.com

通讯作者:
李　典（1990－），男，博士，讲师，主要从事舰船抗爆抗冲击研究. E-mail：lidian916@163.com

中图分类号: O383
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出版历程
- 收稿日期: 2021-07-20
- 修回日期: 2021-08-11
- 录用日期: 2021-08-17

Dynamic Response Characteristics of Aluminum Foam Sandwich Structure under Explosion Load in Cabin

College of Naval Architecture and Ocean Engineering, Naval University of Engineering, Wuhan 430033, Hubei, China

摘要

摘要: 为探索爆炸载荷下舱内夹芯复合结构的动态响应特性与防护效能，采用小尺度舱室结构模型实验，结合有限元数值分析，开展了不同爆炸距离下舱内双层泡沫铝夹芯结构的动响应特性和变形模式研究。分析了不同爆距下舱内爆炸载荷的作用过程和时空分布特性，讨论了在初始冲击波、初始冲击波叠加各壁面二次反射波和舱内爆炸准静态压力3种载荷下泡沫铝夹芯结构的变形模式。爆炸载荷下舱室壁板承受的载荷依次为初始冲击波、各壁面二次反射波和准静态气压。炸药在靠近舱室一端处起爆时，初始冲击波在近端壁的局部效应明显，在远端壁的作用范围更大，与舱室中心爆炸相比，其爆轰产物波动次数更少。泡沫铝夹芯结构的变形过程可分为泡沫芯层压缩、局部凸起变形和整体挠曲变形3个阶段，对应迎爆面板局部凸起叠加整体挠曲大变形、局部凸起叠加整体挠曲大变形和整体挠曲大变形3种变形模式。
- 爆炸力学 /
- 舱内爆炸 /
- 夹芯结构 /
- 泡沫铝 /
- 动响应 /
- 变形模式
Abstract: To study the dynamic response characteristics and protective effectiveness of sandwich composite structure subjected to internal explosion load in a cabin, small scale structure model experiments and finite element numerical simulations were performed, and the propagation and distribution characteristics of the explosion load in the cabin with different blasting distances were analyzed. The dynamic response and deformation mode of the aluminum foam sandwich structure under the initial shock wave, the superposition of reflected shock waves and the quasi-static pressure of the internal explosion were discussed. The experimental and numerical results showed that when the explosive was detonated near one end of the cabin, the localized deformation of the specimen caused by the initial shock wave is significant, while the deformation area of the specimen on the far wall is larger and smoother. Compared with the load conditions of explosions in the center of the cabin, the fluctuation of the shock wave are gentler. In addition, the deformation process of aluminum foam sandwich structure can be divided into three stages: foam core compression, local bulge deformation and overall deflection. The corresponding deformation modes include the facing blast panel with local rising on integral deformation, double panels with local rising on integral and large deformation of integral flexure.
- mechanics of explosion /
- explosion in cabin /
- sandwich structure /
- aluminum foam /
- dynamic response /
- deformation mode

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图 1 实验装置及示意图（单位：mm）

Figure 1. Experimental setup and schematic diagram (unit: mm)

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图 2 泡沫铝夹芯结构尺寸示意图（单位：mm）

Figure 2. Size of aluminum foam sandwich structure (unit：mm)

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图 3 泡沫铝准静态压缩应力-应变曲线

Figure 3. Stress-strain curves of aluminum foams under quasi-static compression experiments

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图 4 面板拉伸试件尺寸（单位：mm）

Figure 4. Dimension of tensile specimen of panel steel (unit: mm)

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图 5 面板拉伸应力-应变曲线

Figure 5. Stress-strain curves of steels under tensile experiments

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图 6 装药布置及爆距示意图

Figure 6. Schematic diagram of explosive support and detonation distance

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图 7 爆炸环境示意图

Figure 7. Diagram of explosion environment

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8 夹芯结构迎、背爆面板变形的数值模拟和实验结果

8. Numerical simulation and experiment results of deformation of front and rear plates in sandwich structure

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图 9 350 mm爆距下舱室内冲击动压的变化

Figure 9. Variation of impact pressure in cabin under 350 mm detonation distance

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图 10 50 mm爆距下舱室内冲击动压的变化过程

Figure 10. Variation of impact pressure in cabin under 50 mm detonation distance

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图 11 典型位置

Figure 11. Location of typical points

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图 12 不同爆距下夹芯结构中心点的压力时程曲线

Figure 12. Time history curves of pressure at center point of sandwich structure under different detonation distances

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图 13 不同爆距下舱室角隅点的压力时程曲线

Figure 13. Time history curves of cabin corner pressure at different detonation distances

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图 14 结构中心点和1/4点的压力时程曲线

Figure 14. Pressure time history curves at the center and quarter points of the structure

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图 15 SoD为50 mm时泡沫铝夹芯结构的变形过程

Figure 15. Deformation of aluminum foam sandwich structure under 50 mm detonation distance

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图 16 SoD为550 mm时泡沫铝夹芯结构的变形过程

Figure 16. Deformation of aluminum foam sandwich structure under 550 mm detonation distance

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图 17 SoD分别为50和550 mm时迎、背爆面板中心点的速度时程曲线

Figure 17. Time history curves of center pointvelocity of front and rear plates when theSoD was 50 and 550 mm, respectively

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图 18 舱内爆炸下泡沫铝夹芯结构的3种典型变形模式

Figure 18. Three typical deformation modes of aluminum foam sandwich structure under explosion in cabin

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图 19 封闭环境下100、150 mm爆距时背爆面板的变形量对比

Figure 19. Comparison of deformation of rear plates under 100 and 150 mm detonation distance in closed environment

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图 20 不同爆炸环境下泡沫铝夹芯结构背爆面板的变形对比

Figure 20. Deformation comparison of rear plate of aluminum foam sandwich structure in different explosion environment

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表 1 泡沫铝的主要力学性能参数

Table 1. Main mechanical properties of aluminum foam

Density/(g·cm⁻³)	Elastic modulus/MPa	Plateau stress/MPa
0.37	70	4.7
0.54	145	9.2
0.75	250	19.0

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表 2 钢板的主要力学性能参数

Table 2. Main mechanical parameters of steel

Density/(g·cm⁻³)	Elastic modulus/GPa	Yield strength/MPa	Ultimate tensile strength/MPa
7.8	194	300	390

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表 3 PLASTIC_KINEMATIC本构模型参数

Table 3. Constitutive model parameters of PLASTIC_KINEMATIC

Density/(g·cm⁻³)	E/GPa	$\nu$	$\sigma$ ₀/MPa	E_h/MPa	D/s⁻¹	$\eta$	$\varepsilon$
7.8	194	0.3	300	250	40.5	5	0.22

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表 4 TNT炸药的状态方程参数

Table 4. Equation of state parameters of TNT

A/GPa	B/GPa	R₁	R₂	$\omega$	E₀₁/(kJ·m⁻³)
371.2	3.231	4.15	0.95	0.3	7×10⁶

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表 5 研究工况

Table 5. Working conditions

Condition No.	Explosive environment	SoD/mm	Method	Core thickness/mm
1	Confined	50	Experiment/FEM	20
2	Confined	100	Experiment/FEM	20
3	Confined	150	Experiment/FEM	20
4	Confined	350	FEM	20
5	Confined	550	FEM	20
6	Vented	50	FEM	20
7	Vented	550	FEM	20
8	Free air burst	50	FEM	20
9	Free air burst	550	FEM	20

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表 6 实验与数值模拟的背爆面板最大挠度对比

Table 6. Experimental and numerical comparison of the maximum deflection of the rear plate

SoD/mm	Maximum deflection/mm		Relative error/%
SoD/mm	Experiment	Simulation	Relative error/%
50	40	31	22.5
100	25	24	4.0
150	26	24	7.7

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