蜂窝夹芯结构用连接接头抗冲击性能研究

张智扬; 赵振宇; 任建伟; 高辉遥

doi:10.21656/1000-0887.450131

蜂窝夹芯结构用连接接头抗冲击性能研究

doi: 10.21656/1000-0887.450131

张智扬^{1, 2,},
赵振宇^{1, 2, ,},
任建伟^{1, 2, 3},
高辉遥^{1, 2}

1.
南京航空航天大学航空航天结构力学及控制国家重点实验室，南京 210016
2.
南京航空航天大学多功能轻量化材料与结构工信部重点实验室，南京 210016
3.
火箭军工程大学，西安 710025

基金项目:

国家自然科学基金 11972185

国家自然科学基金 12002156

详细信息

作者简介:
张智扬(1997—)，男，博士生(E-mail: zhangzy9712@163.com)

通讯作者:
赵振宇(1986—)，男，副研究员，博士(通讯作者. E-mail: zhenyu_zhao@nuaa.edu.com.cn)

中图分类号: O347.1
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- 文章访问数: 194
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- 被引次数: 0
出版历程
- 收稿日期: 2024-05-09
- 修回日期: 2024-06-09
- 刊出日期: 2024-08-01

Study on Impact Resistance of Connection Joints for Honeycomb Sandwich Structures

ZHANG Zhiyang^{1, 2
,},
ZHAO Zhenyu^{1, 2
, ,},
REN Jianwei^{1, 2, 3},
GAO Huiyao^{1, 2}

1.
State Key Laboratory of Mechanics and Control for Aerospace Structures, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, P.R.China
2.
MIIT Key Laboratory of Multifunctional Lightweight Materials and Structures (MLMS), Nanjing University of Aeronautics and Astronautics, Nanjing 210016, P.R.China
3.
PLA Rocket Force University of Engineering, Xi'an 710025, P.R.China

摘要

摘要: 夹层结构在工程领域的应用广泛，但其连接装配问题却日益突出，尤其是面临强动载荷下的作战装备，如何设计连接接头以提升结构的可靠性及维修性，是目前研究的热点. 针对蜂窝夹芯防护结构在典型作战环境中的连接装配问题，设计了一种由方管锁定的快速组装连接接头，并通过泡沫子弹冲击实验以获得连接结构在不同冲量下的动态响应，随后采用有限元方法对冲击试验进行了模拟，仿真结果与实验结果吻合度较好. 在此基础上，利用该有限元模型进一步探讨了方管壁厚、连接单元宽度等几何参数对该结构在泡沫子弹冲击载荷作用下的峰值挠度的影响. 结果表明，较薄方管壁厚(t_t/t_f≤0.375)使得连接结构容易陷入方管压溃的失效模式导致其峰值挠度显著增大，而较小的连接单元宽度(2a/W≤0.267)将导致面板抗拉强度下降，进而削弱连接结构抗冲击性能. 此外，随着连接单元宽度的不断增加，连接结构的峰值挠度呈现先减小后增大的趋势，这是由于连接单元的有效横截面积与机械互锁接触面积之间存在竞争机制. 当前研究表明，这种快速组装连接接头能有效抵御动态冲击载荷，具有抗冲击吸能、便于维护更换的特点，有望应用于各型主战装备防护结构的连接，为夹层连接结构的抗冲击设计提供参考.
- 蜂窝夹芯结构 /
- 连接接头 /
- 快速组装 /
- 抗冲击 /
- 动态力学行为
Abstract: Sandwich structures are widely used in engineering fields, but their connection and assembly problems become more and more prominent, especially for combat equipment under strong dynamic loads. How to design connection joints to improve the reliability and maintainability of the structure is a hot research topic at present. Aimed at the connection and assembly problem of honeycomb sandwich protection structures in typical combat environment, a quick assembly joint locked by square tubes was designed, and the dynamic responses of the connection structure under different impulses were obtained by foam projectile impact tests. Then the finite element method was used to simulate the impact test, and the simulation results agree well with the experimental results. On this basis, the effects of geometric parameters such as wall thicknesses and connection unit widths on the peak deflections of the structure under the foam projectile impacts were further discussed with the finite element model. The results indicate that, the thinner wall thickness(t_t/t_f≤0.375) of the square tube makes the connection structure prone to collapse, leading to a significant increase in peak deflections. However, a smaller width (2a/W≤0.267) of the connection unit causes the panel tensile strength to decrease, thereby weakening the impact resistance of the connection structure. In addition, as the connection unit width increases, the peak deflection of the connection structure will first decrease and then increase. This is due to the competition mechanism between the effective cross-sectional area of the connection unit and the mechanical interlocking contact area. The proposed quick assembly connection joint can effectively resist dynamic impact loads, has good impact energy absorption abilities, and easy maintenance and replacement. It is hopeful to be applied to the connection of various types of main combat equipment protection structures, and provides reference for the impact resistance design of sandwich connection structures.
- honeycomb sandwich structure /
- connection joint /
- quick assembly /
- impact resistance /
- dynamic mechanical behavior

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图 1 连接结构试样

Figure 1. The connection structure specimen

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图 2 连接结构试样制备流程示意图

Figure 2. The preparation process of the connection structure specimen

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图 3 一级轻气炮示意图^[31]

Figure 3. Schematic diagram of the 1st-level light gas gun^[31]

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图 4 泡沫子弹冲击连接结构试样的有限元模型

Figure 4. The finite element model for the foam projectile impact connection structure specimen

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图 5 84.7 m/s工况下仿真模型的网格无关性分析

Figure 5. Grid independence analysis of the simulation model under 84.7 m/s

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图 6 不同冲击速度下连接结构试样的跨中挠度-时程曲线

Figure 6. Mid-span deflection-time curves of connection structure specimens at different impact velocities

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图 7 连接结构试样冲击试验的结构变形演化图

Figure 7. Structural deformation evolutions of connection structure specimen impact tests

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图 8 84.7 m/s冲击速度下的连接结构试样的实验和仿真结果对比

Figure 8. Comparison of experiment and simulation results of connection structure specimens at an 84.7 m/s impact velocity

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图 9 84.7 m/s冲击速度下结构变形演化的有限元仿真结果

Figure 9. Finite element simulation results of structural deformation evolution at an 84.7 m/s impact velocity

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图 10 三种典型接头宽度下，试样的无量纲方管连接件壁厚和无量纲峰值跨中挠度关系

Figure 10. The relationships between demensionless square tube connector wall thicknesses and dimensionless peak mid-span deflections of the specimen under 3 typical joint widths

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图 11 方管压溃失效，对应接头几何尺寸参数2a/W=0.50, t_t/t_f=0.25

Figure 11. The square tube collapse failure, corresponding joint geometric parameters 2a/W=0.50, t_t/t_f=0.25

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图 12 三种典型方管连接件壁厚尺寸下，试样的无量纲齿根宽度和无量纲峰值跨中挠度关系

Figure 12. The relationships between dimensionless root widths and dimensionless peak mid-span deflections of the specimen under 3 typical square tube connector wall thicknesses

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图 13 84.7 m/s冲击速度下，有、无方管连接试样的无量纲化齿根宽度与无量纲化峰值跨中挠度关系

Figure 13. The relationships between the dimensionless root widths and the dimensionless peak mid-span deflections of the specimen with and without square the tube connector at an 84.7 m/s impact velocity

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图 14 84.7 m/s冲击速度下，无方管连接试样发生了分离，对应接头几何尺寸参数2a/W=0.50, t_t/t_f=0.75

Figure 14. At the impact velocity of 84.7 m/s, the separated specimen and the corresponding joint geometric parameters 2a/W=0.50, t_t/t_f=0.75

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表 1 试样各尺寸参数

Table 1. The size parameters of the specimen

parameter	value
connection sample length L/mm	300
clamping end length l/mm	35
sample width W/mm	60
panel thickness t_f/mm	2
honeycomb core height h/mm	14
honeycomb core wall thickness t_c/mm	0.05
honeycomb core side length L_c/mm	2
square tube wall thickness t_t/mm	1.5
diameter opening D/mm	11
root width a/mm	12
addendum width b/mm	18

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表 2 模型中所涉及的材料的Johnson-Cook材料本构参数^{[19, 32-33]}

Table 2. Johnson-Cook material constitutive parameters of the materials involved in the model^{[19, 32-33]}

parameter	304 stainless steel	Q235B steel	AA3003-H18 aluminum alloy
density ρ/(kg·m^-3)	7 800	7 800	2 680
elasticity modulus E/GPa	193	200	67.6
Poisson’s ratio ν	0.3	0.33	0.33
initial yield stress A/MPa	310	293.8	214
hardening constant B/MPa	1 000	230.2	143
hardening exponent n	0.65	0.578	0.36
reference strain rate $\dot{\varepsilon}_0 $/s^-1	0.001	0.002 1	1
strain rate constant C	0.034	0.065 2	0.015
melting temperature T_M/K	1 800	1 793	893
thermal softening exponent m	1.05	0.706	0
specific heat θ/(J·kg^-1·K^-1)	450	440	893

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表 3 泡沫铝的基本性能参数

Table 3. Basic performance parameters of the aluminum foam

parameter	value
density ρ_p/(kg·m^-3)	378
elasticity modulus E_p/GPa	0.38
Poisson’s ratio ν_p	0.45
compressive yield stress ratio R	1.732

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表 4 泡沫铝的Crushable Foam模型参数

Table 4. Crushable Foam model parameters of the aluminum foam

stress in uniaxialcompression σ_axial/MPa	3.457	4.120	4.540	5.186	5.538	6.234	7.086	7.313	7.486	7.629	8.422	11.55
plastic strain in uniaxialcompression ε_axial^pl	0	0.042	0.084	0.126	0.206	0.262	0.310	0.349	0.417	0.456	0.542	0.674

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表 5 连接结构试样的冲击试验数据

Table 5. Impact experiment data of connection structure specimens

specimen number	foam projectile mass m_p/g	initial projectile velocityv₀/(m/s)	initial unit area impulseI₀/(kPa·s)	peak mid-span deflectionδ_m/mm
1#	107.4	84.7	3.44	34.7
2#	108.0	100.7	4.12	35.5
3#	108.3	117.4	4.81	38.9
4#	108.1	154.7	6.33	undetectable

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