温度对金属-复合材料混合多螺栓连接力学性能的影响

王东; 董传瑞; 朱红民; 丁国元; 黄河源; 赵美英

温度对金属-复合材料混合多螺栓连接力学性能的影响

王东¹,
董传瑞¹,
朱红民¹,
丁国元¹,
黄河源^{2, 3, ,},
赵美英²

1.
中国运载火箭技术研究院, 北京 100076
2.
西北工业大学　航空学院, 西安 710072
3.
强度与结构完整性全国重点实验室, 西安 710065

基金项目: 强度与结构完整性全国重点实验室开放基金(ASSIKFJJ202305005)

详细信息

通讯作者:
黄河源，博士，副研究员，硕士生导师，研究方向为飞行器结构设计　E-mail: huangheyuan@nwpu.edu.cn

中图分类号: V214.8
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- 被引次数: 0
出版历程
- 收稿日期: 2023-08-15
- 修回日期: 2023-09-18
- 录用日期: 2023-10-11
- 网络出版日期: 2023-10-21
- 刊出日期: 2024-06-15

Effect of temperature on mechanical properties of metal-compositehybrid multi-bolt joint

1.
China Academy of Launch Vehicle Technology, Beijing 100076, China
2.
School of Aeronautics, Northwestern Polytechnical University, Xi′an 710072, China
3.
National Key Laboratory of Strength andStructural Integrity, Xi′an 710065, China

Funds: National Key Laboratory of Strength and Structural Integrity Open Fund (ASSIKFJJ202305005)

摘要

摘要: 以铝合金-碳纤维/双马来酰亚胺(BMI)树脂复合材料多螺栓双搭接结构为研究对象，结合数字图像相关(DIC)技术开展了不同温度环境下(−100℃、25℃、150℃)的准静态拉伸试验，并采用金属弹塑性模型和复合材料渐进损伤模型进行数值模拟分析，同时开发考虑温度影响的UMAT子程序预测复合材料损伤，研究了温度对金属-复合材料混合多螺栓连接结构承载能力、破坏模式、损伤演化和钉载分配的影响规律。结果表明：相比25℃室温环境，150℃和−100℃环境下结构的极限载荷分别降低4.46%和2.06%；不同温度环境下的破坏模式均为复合材料孔边拉伸断裂，同时高温环境下孔边分层与挤压现象更为严重，而低温环境下纤维与基体结合紧密，孔边挤压与分层现象更弱；150℃环境下复合材料孔边损伤不均匀性相比常温环境有所减弱，而−100℃环境下不均匀性有所增强；由于热膨胀不匹配性，高温和低温环境下三组螺栓钉载分配规律也表现出明显差异。
- 碳纤维/BMI树脂复合材料 /
- 螺栓连接结构 /
- 渐进损伤分析 /
- 高/低温力学性能 /
- 钉载分配
Abstract: Taking the aluminum alloy-carbon fiber/bismaleimide (BMI) resin composite multi-bolt double-lap structure as the research object, combined with digital image correlation (DIC) technology, quasi-static tensile tests under different temperature environments (−100°C, 25°C, 150°C) were carried out. The elastic-plastic model of metal and the progressive damage model of composite were used for numerical simulation. A UMAT subroutine considering the influence of temperature was developed to predict the damage of composite materials. The influence of temperature on load-bearing capacity, failure mode, damage evolution and bolt-load distribution of metal-composite hybrid multi-bolt joint structure was studied. The results show that the maximum load of the structure in the environment of 150°C and −100°C is reduced by 4.46% and 2.06% compared with the room temperature environment of 25°C, respectively. The failure modes of three temperature environments are all tensile fracture of the hole edge of the composite. The delamination and extrusion phenomenon of the hole edge are more serious at the high temperature, but the fiber and the matrix are tightly bonded and the extrusion and delamination of the hole edge are weaker in the cryogenic temperature environment. The unevenness of the multi-bolt hole edge damage is weakened at 150°C and is enhanced at −100°C, compared with at the room temperature. Due to the difference in thermal expansion between metal and composite, the bolt load distribution of the three bolts at high and cryogenic temperatures is different.
- carbon fiber/BMI resin composite /
- bolted joint structure /
- progressive damage analysis /
- high/cryogenic temperature mechanical properties /
- bolt-load distribution

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图 1 试验件形状及尺寸示意图

Figure 1. Schematic diagram of shape and size of test piece

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图 2 试验过程中的温度控制

Figure 2. Temperature control in the test process

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图 3 DIC测试设备

Figure 3. Digital image correlation test equipment

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图 4 金属与复合材料混合多螺栓连接有限元模型

Figure 4. Finite element model of metal-composite hybrid multi-bolt joint

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图 5 不同温度环境下2024 Al应力-应变曲线

Figure 5. Stress-strain curves of 2024 Al in different temperature environment

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图 6 碳纤维/BMI树脂复合材料搭接板宏观破坏模式

Figure 6. Macroscopic failure mode of carbon fiber/BMI resin composite laminates

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图 7 不同温度环境下碳纤维/BMI树脂复合材料搭接板破坏后的孔边SEM图像

Figure 7. SEM images of hole edges of carbon fiber/BMI resin composite laminates after failure at different temperature environments

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图 8 混合连接结构受载过程中的表面应变场分布

Figure 8. Distribution of surface strain field in the process of hybrid joint structure loading

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图 9 25℃环境下碳纤维/BMI树脂复合材料孔边损伤演化过程图

Figure 9. Damage evolution process diagram of carbon fiber/BMI resin composite material hole edge at 25℃

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图 10 不同温度环境下碳纤维/BMI树脂复合材料孔边纤维损伤演化过程图

Figure 10. Damage evolution process diagram of carbon fiber/BMI resin composite material hole edge at different temperature

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图 11 不同温度下混合多螺栓连接的钉载比例变化规律

Figure 11. Variation law of bolt-load distribution ratio of mixed multi-bolt joint structure at different temperature

Bolt1/ Bolt 2/ Bolt 3 in Fig. 11 corresponds to Hole1/ Hole 2/ Hole 3 in Fig. 6, respectively

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表 1 碳纤维/BMI树脂基复合材料属性参数^{[14, 24]}

Table 1. Attribute parameters of carbon fiber/BMI resin composite^{[14, 24]}

	${E_{11}}/{\text{MPa}} $	${E}_{22}、{E}_{33}/\text{MPa} $	${G}_{12}、{G}_{13}/\text{MPa} $	$ {G_{23}}/{\text{MPa}} $	$ {\nu }_{12}、{\nu }_{13} $	${\nu _{23}} $
150℃	123000	9106	5250	3133	0.33	0.42
25℃	125000	9370	5450	3373	0.3	0.4
−100℃	129000	9980	5660	3521	0.28	0.38
	${X_{\text{t}}}/{\text{MPa}} $	$ {Y}_{\text{t}}、{Z}_{\text{t}}/\text{MPa} $	${X_{\text{c}}}/{\text{MPa}} $	$ {Y}_{\text{c}}、{Z}_{\text{c}}/\text{MPa} $	$ {S}_{12}、{S}_{13}/\text{MPa} $	${S_{23}}/{\text{MPa}} $
150℃	2180	1365	70	235	148	87
25℃	2424	1430	74	248	159	95
−100℃	2298	1510	68	260	167	90
Notes: $ {E_{11}},{E_{22}},{E_{33}} $−Elastic modulus in directions 1, 2 and 3; ${G_{12}},{G_{13}},{G_{23}} $−Shear modulus in directions 12, 13 and 23; ${\nu }_{12},{\nu }_{13},{\nu }_{23} $−Poisson's ratio in directions 12, 13 and 23, ${X_{\text{t}}},{Y_{\text{t}}},{Z_{\text{t}}} $−Tensile strength in directions x, y and z; ${X_{\text{c}}},{Y_{\text{c}}},{Z_{\text{c}}} $−Compressive strength in directions x, y and z; $ {S}_{12},{S}_{13},{S}_{23} $−Shear strength in directions 12, 13 and 23.

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表 2 材料热膨胀系数^[14]

Table 2. Thermal expansion coefficient of materials^[14]

Material	Aluminum alloy	TC4	Composite (Fiber direction)	Composite (Matrix direction)
Thermal expansivity/(10⁻⁶K⁻¹)	25	8.1	0.25	32.6

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表 3 混合连接结构极限载荷F_max试验值与仿真值对比

Table 3. Comparison between test value and simulation value of maximum load of hybrid joint structures

Temperature	Maximum load average/kN	Dispersion coefficient/%	Simulate maximum load/kN	Error/%
150℃	40.51	2.94	39.45	2.6
25℃	42.74	0.92	40.81	4.5
−100℃	41.87	6.37	39.84	4.8

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