金属/复合材料混合连接结构高温承载特性与失效行为研究

戴亚光; 王东; 万小朋; 黄河源

doi:10.13433/j.cnki.1003-8728.20230269

金属/复合材料混合连接结构高温承载特性与失效行为研究

doi: 10.13433/j.cnki.1003-8728.20230269

戴亚光^{1, 2,},
王东¹,
万小朋¹,
黄河源^1, ,

1.
西北工业大学航空学院, 西安 710072
2.
中国航空工业集团公司沈阳飞机设计研究所综合强度部, 沈阳 110035

基金项目:

中央高校基本科研业务费专项 D5000230052

详细信息

作者简介:
戴亚光(1981-), 高级工程师, 研究方向为飞机强度设计与验证, daisy1981sy@163.com

通讯作者:
黄河源, 副研究员, 硕士生导师, huangheyuan@nwpu.edu.cn

中图分类号: V258⁺.3
计量
- 文章访问数: 90
- HTML全文浏览量: 55
- PDF下载量: 19
- 被引次数: 0
出版历程
- 收稿日期: 2022-08-23
- 刊出日期: 2023-10-25

High-temperature Load-bearing Characteristics and Failure Behavior of Metal/composite Hybrid Connection Structures

DAI Yaguang^{1, 2
,},
WANG Dong¹,
WAN Xiaopeng¹,
HUANG Heyuan^{1
, ,}

1.
School of Aviation, Northwestern Polytechnical University, Xi′an 710072, China
2.
General Strength Department, Shenyang Aircraft Design and Research Institute, Aviation Industry Corporation of China, Shenyang 110035, China

摘要

摘要: 针对3种不同搭接板厚度的铝合金和碳纤维增强树脂(Carbon fiber reinforced polymers, CFRP)复合材料三钉螺栓连接结构, 分别进行了常温(25 ℃)和高温(150 ℃)环境下的准静态拉伸力学性能测试。同时建立有限元三维模型, 结合Hashin失效准则和渐进损伤准则进行数值模拟分析, 获得了结构的高温承载特性与损伤演化规律。研究结果表明, 对于D₁、D₂、D₃这3种不同铝合金厚度的连接结构, 在150 ℃时的极限载荷试验值相对25 ℃分别降低6.63%、13.07%、8.48%, 且常温环境下3种结构破坏模式分别为铝合金拉伸断裂、复合材料挤压失效、复合材料拉伸断裂, 而在150 ℃高温环境下, 3种结构损伤模式都为复合材料孔边的挤压剪切失效。
- 碳纤维增强树脂复合材料 /
- 复合材料螺栓连接结构 /
- 高温力学性能 /
- 损伤失效行为 /
- 渐进损伤模型
Abstract: The quasi-static tensile mechanical properties tests at room temperature (25 ℃) and high temperature (150 ℃) were carried out for the three-nail bolted connection structures of aluminum alloys and carbon fiber reinforced polymers (CFRP) composites with different lap plate thicknesses, respectively. At the same time, a three-dimensional finite element model was established, and the Hashin failure criterion and progressive damage criterion were used for numerical simulation analysis, and the high temperature bearing characteristics and damage evolution law of the structure were obtained. The results show that for the connection structures of the three different aluminum alloy thicknesses D₁, D₂, and D₃, the ultimate load test values at 150 ℃ relative to 25 ℃ were reduced by 6.63%, 13.07%, and 8.48%, respectively. The damages of the three structural destruction modes were aluminum alloy tensile fracture, composite extrusion failure, and composite tensile fracture at 25 ℃ respectively, while the three structural damage modes are the extrusion shear failure of the composite hole edge at 150 ℃.
- carbon fiber reinforced polymer composites /
- composite bolted structures /
- high temperature mechanical properties /
- damage failure behavior /
- progressive damage model

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图 1 试验件示意图

Figure 1. Schematic diagram of the test piece

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图 2 试验件夹持形式及试验环境箱

Figure 2. Test piece clamping form and test environment

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图 3 铝合金与复合材料螺栓连接结构有限元分析模型

Figure 3. Finite element analysis model of aluminum alloy and its composite bolted structure

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图 4 25 ℃环境下CFRP复合材料和铝合金螺栓连接结构的破坏样貌

Figure 4. Failure pattern of CFRP composite materials and aluminum alloy bolted structure under 25 ℃ environment

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图 5 150 ℃环境下CFRP复合材料和铝合金螺栓连接结构的破坏样貌

Figure 5. Failure pattern of CFRP composite materials and aluminum alloy bolted connection structure at 150 ℃

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图 6 150 ℃高温环境下D₂结构的损伤演化过程

Figure 6. Damage evolution of D₂ structure at 150 ℃

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图 7 铝合金面板厚度对结构极限载荷的影响曲线

Figure 7. Influence of aluminum alloy panel thickness on the ultimate load of the structure

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图 8 温度对结构承载能力的影响图

Figure 8. Influence of temperature on the bearing capacity of the structure

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表 1 试验件尺寸及试验矩阵

Table 1. Test piece size and test matrix

编号	几何尺寸/mm
编号	t_m	t_c	e	p	l	d	g	w
D₁	1.5
D₂	2.0	2.5	18	30	200	6	50	36
D₃	2.5

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表 2 2024铝合金弹塑性模型参数

Table 2. 2024 aluminum alloy elastoplastic model parameters

屈服应力/MPa	260	279	294	313	340	380	427
塑性应变	0	0.000 413	0.001 036	0.002 651	0.008 131	0.022 934	0.044 134

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表 3 CFRP复合材料力学性能参数^[18]

Table 3. Mechanical property parameters of CFRP composites^[18]

性能	数值	强度	数值
纵向弹性模量E₁₁/GPa	146.22	纵向拉伸强度X_t/MPa	1 986
纵向弹性模量E₂₂, E₃₃/GPa	10.84	横向、厚度方向拉伸强度Y_t、Z_t/MPa	58
面内剪切模量G₁₂, G₁₃/GPa	5.62	纵向压缩强度X_c/MPa	1 349
面外剪切模量G₂₃/GPa	9.34	横向、厚度方向压缩强度Y_c、Z_c/MPa	255
泊松比υ₁₂, υ₁₃, υ₂₃	0.30, 0.30, 0.42	面内剪切强度S₁₂/MPa	105

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表 4 材料热膨胀系数^[18]

Table 4. Thermal expansion coefficient of materials^[18]

参数	2024铝合金	TC4钛合金	复合材料(纤维方向)	复合材料(基体方向)
热膨胀系数/10^-6 K^-1	25	8.1	0.25	32.6

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表 5 复合材料损伤准则及刚度退化模型^[19]

Table 5. Composite damage criteria and stiffness degradation model^[19]

失效模式	损伤准则	刚度退化
纤维拉伸失效(σ₁₁＞0)		E₁₁=0.07E₁₁
纤维压缩失效(σ₁₁＜0)		E₁₁=0.14E₁₁
基体拉伸失效(σ₂₂＞0)		E₂₂=0.2E₂₂, G₁₂=0.2G₁₂, G₂₃=0.2G₂₃
基体压缩失效(σ₂₂＜0)		E₂₂=0.4E₂₂, G₁₂=0.4G₁₂, G₂₃=0.4G₂₃

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表 6 数值仿真与试验结果比较

Table 6. Comparison of numerical simulation and test results

结构形式	D₁(t_m=1.5 mm)		D₂(t_m=2.0 mm)		D₃(t_m=2.5 mm)
温度/℃	25	150	25	150	25	150
试验值F_max/kN	38.74	36.17	43.85	38.12	44.23	40.48
仿真值F_max/kN	36.73	35.79	40.24	39.55	40.62	39.15
误差/%	5.19	1.05	8.23	-3.75	8.16	3.29
断裂模式	铝板断	复合材料剪切失效	复合材料挤压失效	复合材料剪切失效	复合材料拉伸断裂	复合材料剪切失效

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参考文献(19)

[1]	周亦人, 沈自才, 齐振一, 等. 中国航天科技发展对高性能材料的需求[J]. 材料工程, 2021, 49(11): 41-50. doi: 10.11868/j.issn.1001-4381.2021.000129 ZHOU Y R, SHEN Z C, QI Z Y, et al. Demand for high performance materials in development of China's aerospace science and technology[J]. Journal of Materials Engineering, 2021, 49(11): 41-50. (in Chinese) doi: 10.11868/j.issn.1001-4381.2021.000129
[2]	SZIROCZAK D, SMITH H. A review of design issues specific to hypersonic flight vehicles[J]. Progress in Aerospace Sciences, 2016, 84: 1-28. doi: 10.1016/j.paerosci.2016.04.001
[3]	王东, 黄河源, 徐一新, 等. 高温环境下钛合金点阵结构热力耦合性能与失效机理研究[J]. 西北工业大学学报, 2022, 40(1): 25-32. https://www.cnki.com.cn/Article/CJFDTOTAL-XBGD202201003.htm WANG D, HUANG H Y, XU Y X, et al. Study on thermal-mechanical coupling performance and failure mechanism of titanium alloy lattice structures in high temperature environment[J]. Journal of Northwestern Polytechnical University, 2022, 40(1): 25-32. (in Chinese) https://www.cnki.com.cn/Article/CJFDTOTAL-XBGD202201003.htm
[4]	周志勇, 马彬, 张萃, 修等. X-37B轨道试验飞行器可重复使用热防护系统综述[J]. 航天器工程, 2016, 25(4): 95-101. ZHOU Z Y, MA B, ZHANG C, et al. Reusable thermal protection system for orbital test vehicle X-37B[J]. Spacecraft Engineering, 2016, 25(4): 95-101. (in Chinese)
[5]	高禹, 张志松, 王柏臣, 等. 空天飞行器用炭/双马复合材料环境损伤行为的研究现状[J]. 高分子材料科学与工程, 2013, 29(6): 165-168. GAO Y, ZHANG Z S, WANG B C, et al. Investigation of the environmental damage behaviors for carbon//ismaleimide composite used in aerospace flying vehicle[J]. Polymer Materials Science and Engineering, 2013, 29(6): 165-168. (in Chinese)
[6]	ZHOU Y H, YAZDANI-NEZHAD H, MCCARTHY M A, et al. A study of intra-laminar damage in double-lap, multi-bolt, composite joints with variable clearance using continuum damage mechanics[J]. Composite Structures, 2014, 116: 441-452. doi: 10.1016/j.compstruct.2014.05.051
[7]	王强, 贾普荣, 张龙, 刚等. 碳纤维增强复合材料沉头螺栓连接失效分析[J]. 航空材料学报, 2020, 40(6): 59-70. WANG Q, JIA P, ZHANG L, et al. Failure analysis of carbon fiber reinforced composite countersunk bolt joint[J]. Journal of Aeronautical Materials, 2020, 40(6): 59-70. (in Chinese)
[8]	LI D S, ZHAO C Q, JIANG N, et al. Effect of temperature on bending properties and failure mechanism of three-dimensional multiaxial warp-knitted carbon/epoxy composites[J]. High Performance Polymers, 2016, 28(2): 239-252. doi: 10.1177/0954008315579471
[9]	宋健, 温卫东. 不同温度下树脂基复合材料层合板力学性能试验[J]. 航空动力学报, 2016, 31(4): 1006-1018. https://www.cnki.com.cn/Article/CJFDTOTAL-HKDI201604032.htm SONG J, WEN W D. Experiment on mechanical properties of resin matrix composites laminates under various temperatures[J]. Journal of Aerospace Power, 2016, 31(4): 1006-1018. (in Chinese) https://www.cnki.com.cn/Article/CJFDTOTAL-HKDI201604032.htm
[10]	CHENG X Q, LIU S F, ZHANG J K, et al. Hygrothermal effects on mechanical behavior of scarf repaired carbon-epoxy laminates subject to axial compression loads: Experiment and numerical simulation[J]. Polymer Composites, 2018, 39(3): 904-914. doi: 10.1002/pc.24017
[11]	YANG B F, YUE Z F, GENG X L, et al. Temperature effects on transverse failure modes of carbon fiber/bismaleimides composites[J]. Journal of Composite Materials, 2017, 51(2): 261-272. doi: 10.1177/0021998316639122
[12]	ZHANG J, ROWLAND J. Damage modeling of carbon-fiber reinforced polymer composite pin-joints at extreme temperatures[J]. Composite Structures, 2012, 94(8): 2314-2325. doi: 10.1016/j.compstruct.2012.03.011
[13]	徐鲁兵, 张宏建, 吕文礼, 东等. 高温下复合材料螺栓接头强度的试验研究[J]. 装备环境工程, 2017, 14(9): 48-52. XU L B, ZHANG H J, LYU W L, et al. Experimental study on strength of bolted joint of composites at elevated temperature[J]. Equipment Environmental Engineering, 2017, 14(9): 48-52. (in Chinese)
[14]	ZU S M, ZHOU Z G, ZHAO Y, et al. Effect of temperature and geometrical parameters on mechanical properties of pin-loaded fiber metal laminate joints[J]. Journal of Composite Materials, 2017, 51(22): 3163-3173. doi: 10.1177/0021998316687029
[15]	邓文亮, 成竹, 唐虎. 复合材料/金属混合结构热应力分布规律[J]. 应用力学学报, 2020, 37(2): 550-557. https://www.cnki.com.cn/Article/CJFDTOTAL-YYLX202002012.htm DENG W L, CHENG Z, TANG H. Thermal stress distribution law of hybrid composite metal structures[J]. Chinese Journal of Applied Mechanics, 2020, 37(2): 550-557. (in Chinese) https://www.cnki.com.cn/Article/CJFDTOTAL-YYLX202002012.htm
[16]	朱梓珣. 飞机复合材料层合板与金属连接结构热效应分析[D]. 哈尔滨: 哈尔滨工业大学, 2019. ZHU Z X. Thermal effect analysis of composite laminates and metal connections for aircraft[D]. Harbin: Harbin Institute of Technology, 2019. (in Chinese)
[17]	ASTM D5961/D5961M-17 Standard test method for bearing response of polymer matrix composite laminates[S]. America: American Society of Testing Materials, 2017.
[18]	杨白凤. 碳纤维/双马树脂基复合材料及其连接结构在空天环境温度下的力学行为[D]. 西安: 西北工业大学, 2018. YANG B F. Mechanical behaviour of carbon fiber/BMI composites and joints at space environment temperature[J]. Xi'an: Northwestern Polytechnical University, 2018. (in Chinese)
[19]	CHENG X Q, YANG M M, ZHANG J, et al. Thermal behavior and tensile properties of composite joints with bonded embedded metal plate under thermal circumstance[J]. Composites Part B: Engineering, 2016, 99: 340-347.