修复参数对复合材料胶接金属残余热应力的影响

刘鹏; 魏莉莉; 苗春贺; 薛晓; 孙运刚; 宣善勇; 单奕萌

doi:10.13224/j.cnki.jasp.20240815

修复参数对复合材料胶接金属残余热应力的影响

doi: 10.13224/j.cnki.jasp.20240815

刘鹏^{1, 2,},
魏莉莉³,
苗春贺^{1, 2,*, ,},
薛晓^{1, 2},
孙运刚^{1, 2},
宣善勇^{1, 2},
单奕萌^{1, 2}

1.
国营芜湖机械厂，安徽芜湖 241007
2.
安徽省航空复合材料维修工程技术研究中心，安徽芜湖 241007
3.
中部战区空军保障部，北京 100005

详细信息

作者简介:
刘鹏（1971-），男，高级工程师，硕士，主要从事航空装备修理研究。E-mail：2920041153@qq.com

通讯作者:
苗春贺（1994-），男，工程师，博士，主要从事航空装备修理与复合材料损伤修复设计研究。E-mail：mch@mail.ustc.edu.cn

中图分类号: V256.7
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- 被引次数: 0
出版历程
- 收稿日期: 2024-12-01
- 网络出版日期: 2025-08-02

Influence of repair parameters on residual thermal stress of composite bonded metal

LIU Peng^{1, 2
,},
WEI Lili³,
MIAO Chunhe^{1, 2,*
, ,},
XUE Xiao^{1, 2},
SUN Yungang^{1, 2},
XUAN Shanyong^{1, 2},
SHAN Yimeng^{1, 2}

1.
Wuhu State-owned Factory of Machining，Wuhu Anhui 241007，China
2.
Anhui Province Aircraft Composite Structure Repair Engineering and Technology Research Center，Wuhu Anhui 241007，China
3.
Central Theater Command Air force Support Department Field Office，Beijing 100005，China

摘要

摘要:
针对复合材料胶接修复金属裂纹损伤过程中，因材料刚度不协调、热膨胀系数不匹配造成的残余热应力控制难题，以CCF300/QY8911复合材料单面胶接含裂纹铝合金板为研究对象，考虑J-349-1胶黏剂的固化动力学行为，借助有限元仿真手段分析了复合材料补片厚度、铺层以及固化制度对复合材料胶接含裂纹金属修复板残余热应力的影响，并完成了原位固化变形监测。结果表明：残余热应力对修复板的抗拉强度、伸长率以及抗疲劳性能均有负面影响；在满足静力变形协调修理原则下，复合材料补片厚度对残余热应力的影响较大，铺层设计对修复板残余热应力的影响并不明显，而固化制度对修复板残余热应力的影响较大，其中两段式固化工艺能够在保证修理效率的前提下，有效降低金属板的残余热应力，该结论可为维修工艺优化提供良好依据。
- 复合材料 /
- 胶接固化 /
- 残余热应力 /
- 修理参数 /
- 变形监测
Abstract:
In order to solve the residual thermal stress control problem caused by uncoordinated material stiffness and mismatching of thermal expansion coefficient in the process of repairing metal crack damage by bonding composite materials, CCF300/QY8911 composite material bonded single-sided cracked aluminum alloy plate was taken as the research object, and the curing dynamic behavior of J-349-1 adhesive was considered. By means of finite element simulation, the effects of patch thickness, ply and curing regime on residual thermal stress of composite bonded metal repaired plate with cracks were analyzed, and in-situ curing deformation monitoring was completed. The results showed that the residual thermal stress had negative effects on the tensile strength, elongation and fatigue resistance of the repaired plate. Under the principle of static deformation coordination repair, the thickness of the composite patch had a great influence on the residual thermal stress, but the ply design had no obvious influence on the residual thermal stress of the repaired plate. The curing system had a great influence on the residual thermal stress of the repaired plate, and the two-stage curing process can effectively reduce the residual thermal stress of the metal plate under the premise of ensuring the repair efficiency. The conclusion can provide a good basis for the optimization of the repair process.
- composite /
- bonding curing /
- residual thermal stress /
- repair parameters /
- deformation monitoring

HTML

图 1 复合材料单面胶接含裂纹铝合金试样（单位：mm）

Figure 1. Composite materials bonded single-sided cracked aluminum alloy specimens （unit：mm）

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图 2 复合材料胶接金属板三维仿真模型

Figure 2. 3D simulation model of composite bonded metal plate

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图 3 固化应变测量系统及应变仪排布

Figure 3. Arrangement of curing strain measurement system and strain gauge

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图 4 3种固化温度-时间曲线

Figure 4. Three curing temperature-time curves

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图 5 HZD 修复板的固化后残余热应力分布

Figure 5. Results of curing residual thermal stress of HZD repair panels

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图 6 3种试件的拉伸载荷-位移曲线

Figure 6. Tensile load-displacement curves of three specimens

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图 7 3种试件的裂尖应力-载荷曲线

Figure 7. Crack tip stress-load curves of three specimens

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图 8 353.15 K/3 h应变监测结果

Figure 8. Results of strain monitoring at 353.15 K/3 h

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图 9 3种铺层/厚度补片下残余热应力仿真结果

Figure 9. Simulation results of residual thermal stress under three kinds of ply/thickness patches

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图 10 两种固化制度下升温过程应变-温度分布

Figure 10. Strain-temperature distribution during the heating process under two curing regimes

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图 11 3种固化制度下降温过程中铝合金试样的残余热应力/应变随温度的变化趋势

Figure 11. Residual thermal stress/strain of aluminum alloy specimens with temperature during the temperature reduction process of the three curing regimes

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表 1 J-349-1胶黏剂和铝合金板的性能参数

Table 1. Performance parameters of J-349-1 adhesive and aluminum alloy plate

材料	ρ/（g/cm³）	c/（J/（g·K））	α/10⁻⁶ K⁻¹	E/GPa	ν
7B04-T6	2.8	0.9	23	72.2	0.33
J-349-1	1.59	1.46	79.3	2.62	0.35

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表 2 含不同铺层和厚度的复合材料补片的等效材料参数

Table 2. Equivalent material parameters of composite patches with different plies and thicknesses

复合材料铺层	d_cf/mm	E₁₁/MPa	E₂₂/MPa	G₁₂/MPa	ν₁₂	α₁₁/10⁻⁶ K⁻¹	α₂₂/10⁻⁶ K⁻¹	α₃₃/10⁻⁶ K⁻¹
[0]₁₆	2	151 000	9 500	6 900	0.32	1	33	33
[0/90]_{8 s}	4	80 654	80 654	6 900	0.038	3.4	3.4	0
[0/45/90/−45/0/90/45/0]_{2 s}	4	73 311	56 282	18 402	0.238	3.9	4.3	−1.9

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表 3 不同铺层/厚度复合材料补片修复板的固化残余热应力（固化制度：353.15 K/3 h）

Table 3. Residual thermal stress of curing composite patch repair plates with different plies/thicknesses （curing regime: 353.15 K/3 h）

补片类型	模拟结果/MPa	试验结果/MPa	误差/%
HZD	7.82	8.35	6.35
HZZ	11.13	11.95	6.86
HZH	11.13	11.62	4.22
注：误差为实测结果和仿真结果的差值与实测结果的比值。

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参考文献(25)

[1]	吴涵林, 杨际申, 姚改成, 等. 胶接修复工艺的复合材料外涵机匣强度分析[J]. 航空动力学报, 2023, 38(3): 569-577. WU Hanlin, YANG Jishen, YAO Gaicheng, et al. Strength analysis of composite bypass casing of aero-engine in adhesive bonded repair[J]. Journal of Aerospace Power, 2023, 38(3): 569-577. (in Chinese WU Hanlin, YANG Jishen, YAO Gaicheng, et al. Strength analysis of composite bypass casing of aero-engine in adhesive bonded repair[J]. Journal of Aerospace Power, 2023, 38(3): 569-577. (in Chinese)
[2]	邹田春, 李龙辉, 符记, 等. 纤维铺层方式对CFRP-铝合金单搭接胶接接头拉伸性能影响[J]. 航空动力学报, 2022, 37(9): 1905-1914. ZOU Tianchun, LI Longhui, FU Ji, et al. Effect of fiber layup methods on tensile properties of CFRP-aluminum alloy single-lap adhesive joint[J]. Journal of Aerospace Power, 2022, 37(9): 1905-1914. (in Chinese ZOU Tianchun, LI Longhui, FU Ji, et al. Effect of fiber layup methods on tensile properties of CFRP-aluminum alloy single-lap adhesive joint[J]. Journal of Aerospace Power, 2022, 37(9): 1905-1914. (in Chinese)
[3]	宣善勇. 复合材料修理飞机金属结构技术的应用进展[J]. 化工新型材料, 2020, 48(11): 227-229. XUAN Shanyong. Process on boned repair of aircraft metallic structure applied by composite[J]. New Chemical Materials, 2020, 48(11): 227-229. (in Chinese XUAN Shanyong. Process on boned repair of aircraft metallic structure applied by composite[J]. New Chemical Materials, 2020, 48(11): 227-229. (in Chinese)
[4]	汪愿, 孙运刚, 符彬, 等. 基于VARI工艺的碳纤维复合材料快速修理飞机铝合金裂纹的研究[J]. 材料导报, 2024, 38(6): 211-216. WANG Yuan, SUN Yungang, FU Bin, et al. Research on rapid repair of aircraft aluminum alloy cracks with carbon fiber composites based on VARI process[J]. Materials Reports, 2024, 38(6): 211-216. (in Chinese WANG Yuan, SUN Yungang, FU Bin, et al. Research on rapid repair of aircraft aluminum alloy cracks with carbon fiber composites based on VARI process[J]. Materials Reports, 2024, 38(6): 211-216. (in Chinese)
[5]	ZHOU Wei, JI Xiaolong, YANG Sa, et al. Review on the performance improvements and non-destructive testing of patches repaired composites[J]. Composite Structures, 2021, 263: 113659. doi: 10.1016/j.compstruct.2021.113659
[6]	ALBAT A M, ROMILLY D P, RAIZENNE M D. Thermal residual stresses in bonded composite repairs on cracked metal structures[J]. Materials Technology, 2000, 15(4): 299-308. doi: 10.1080/10667857.2000.11752896
[7]	HOSSEINI-TOUDESHKY H, MOHAMMADI B. Thermal residual stresses effects on fatigue crack growth of repaired panels bounded with various composite materials[J]. Composite Structures, 2009, 89(2): 216-223. doi: 10.1016/j.compstruct.2008.07.029
[8]	WANG C H, ROSE L R F, CALLINAN R, et al. Thermal stresses in a plate with a circular reinforcement[J]. International Journal of Solids and Structures, 2000, 37(33): 4577-4599. doi: 10.1016/S0020-7683(99)00175-4
[9]	FREDELL R S. Damage-tolerant repair techniques for pressurized aircraft fuselages [D]. Delft, Netherlands: Technische Universiteit Delft, 1994.
[10]	DAVERSCHOT D R, VLOT A, WOERDEN H J M. Thermal residual stresses in bonded repairs[J]. Applied Composite Materials, 2002, 9(3): 179-197. doi: 10.1023/A:1014790304207
[11]	LOOS A C, SPRINGER G S. Curing of epoxy matrix composites[J]. Journal of Composite Materials, 1983, 17(2): 135-169. doi: 10.1177/002199838301700204
[12]	BOGETTI T A, GILLESPIE J. Two-dimensional cure simulation of thick thermosetting composites[J]. Journal of Composite Materials, 1991, 25(3): 239-273. doi: 10.1177/002199839102500302
[13]	张纪奎, 关志东, 郦正能. 热固性复合材料固化过程中温度场的三维有限元分析[J]. 复合材料学报, 2006, 23(2): 175-179. ZHANG Jikui, GUAN Zhidong, LI Zhengneng. Three-dimensional finite element analysis for the temperature field of thermoset composites during cure process[J]. Acta Materiae Compositae Sinica, 2006, 23(2): 175-179. (in Chinese doi: 10.3321/j.issn:1000-3851.2006.02.030 ZHANG Jikui, GUAN Zhidong, LI Zhengneng. Three-dimensional finite element analysis for the temperature field of thermoset composites during cure process[J]. Acta Materiae Compositae Sinica, 2006, 23(2): 175-179. (in Chinese) doi: 10.3321/j.issn:1000-3851.2006.02.030
[14]	JOSHI S C, LAM Y C. Integrated approach for modelling cure and crystallization kinetics of different polymers in 3D pultrusion simulation[J]. Journal of Materials Processing Technology, 2006, 174(1/2/3): 178-182.
[15]	CHEUNG A, YU Y, POCHIRAJU K. Three-dimensional finite element simulation of curing of polymer composites[J]. Finite Elements in Analysis and Design, 2004, 40(8): 895-912. doi: 10.1016/S0168-874X(03)00119-7
[16]	ALBEDAH A, BACHIR BOUIADJRA B, AMINALLAH L, et al. Numerical analysis of the effect of thermal residual stresses on the performances of bonded composite repairs in aircraft structures[J]. Composites Part B: Engineering, 2011, 42(3): 511-516. doi: 10.1016/j.compositesb.2010.11.013
[17]	AMINALLAH L, ACHOUR T, BACHIR BOUIADJRA B, et al. Analysis of the distribution of thermal residual stresses in bonded composite repair of metallic aircraft structures[J]. Computational Materials Science, 2009, 46(4): 1023-1027. doi: 10.1016/j.commatsci.2009.05.008
[18]	FU Yutong, GAO Xuhao, YAO Xuefeng. Mesoscopic simulation on curing deformation and residual stresses of 3D braided composites[J]. Composite Structures, 2020, 246: 112387. doi: 10.1016/j.compstruct.2020.112387
[19]	LI Jun, YAO Xuefeng, LIU Yinghua, et al. A study of the integrated composite material structures under different fabrication processing[J]. Composites Part A: Applied Science and Manufacturing, 2009, 40(4): 455-462. doi: 10.1016/j.compositesa.2008.10.022
[20]	薛晓, 孙运刚, 宣善勇. 复合材料梯形胶接共固化分析及多目标优化[J]. 航空动力学报, 2024, 39(12): 20220921. XUE Xiao, SUN Yungang, XUAN Shanyong. Analysis and multi-objective optimization of the scarf bonded composite co-curing process[J]. Journal of Aerospace Power, 2024, 39(12): 20220921. (in Chinese XUE Xiao, SUN Yungang, XUAN Shanyong. Analysis and multi-objective optimization of the scarf bonded composite co-curing process[J]. Journal of Aerospace Power, 2024, 39(12): 20220921. (in Chinese)
[21]	牛勇, 穆志韬, 李旭东, 等. 含裂纹金属板复合材料胶接修补结构残余热应力分析[J]. 玻璃钢/复合材料, 2016(5): 23-29. NIU Yong, MU Zhitao, LI Xudong, et al. Thermal residual stress analysis of bonded composite repairs to cracked metallic plate[J]. Fiber Reinforced Plastics/Composites, 2016(5): 23-29. (in Chinese NIU Yong, MU Zhitao, LI Xudong, et al. Thermal residual stress analysis of bonded composite repairs to cracked metallic plate[J]. Fiber Reinforced Plastics/Composites, 2016(5): 23-29. (in Chinese)
[22]	杨晓华, 张玎, 刘学君. 复合材料胶补飞机损伤金属结构疲劳寿命分析[J]. 南京航空航天大学学报, 2017, 49(3): 428-433. YANG Xiaohua, ZHANG Ding, LIU Xuejun. Analysis of fatigue life of damaged aircraft metallic structure repaired with single-side adhesively bonded composite[J]. Journal of Nanjing University of Aeronautics & Astronautics, 2017, 49(3): 428-433. (in Chinese YANG Xiaohua, ZHANG Ding, LIU Xuejun. Analysis of fatigue life of damaged aircraft metallic structure repaired with single-side adhesively bonded composite[J]. Journal of Nanjing University of Aeronautics & Astronautics, 2017, 49(3): 428-433. (in Chinese)
[23]	梁重云, 曾竟成, 肖加余, 等. 复合材料补片胶接修补研究进展[J]. 宇航材料工艺, 2002, 32(4): 7-11. LIANG Chongyun, ZENG Jingcheng, XIAO Jiayu, et al. Progress in bonded composite-patch repair[J]. Aerospace Materials & Technology, 2002, 32(4): 7-11. (in Chinese doi: 10.3969/j.issn.1007-2330.2002.04.002 LIANG Chongyun, ZENG Jingcheng, XIAO Jiayu, et al. Progress in bonded composite-patch repair[J]. Aerospace Materials & Technology, 2002, 32(4): 7-11. (in Chinese) doi: 10.3969/j.issn.1007-2330.2002.04.002
[24]	王遵, 肖加余, 曾竟成, 等. 复合材料胶接修复金属构件残余热应力研究进展[J]. 机械工程材料, 2007, 31(4): 5-8. WANG Zun, XIAO Jiayu, ZENG Jingcheng, et al. Advances in research of thermal residual stresses in bonded composite repairs of metallic components[J]. Materials for Mechanical Engineering, 2007, 31(4): 5-8. (in Chinese doi: 10.3969/j.issn.1000-3738.2007.04.002 WANG Zun, XIAO Jiayu, ZENG Jingcheng, et al. Advances in research of thermal residual stresses in bonded composite repairs of metallic components[J]. Materials for Mechanical Engineering, 2007, 31(4): 5-8. (in Chinese) doi: 10.3969/j.issn.1000-3738.2007.04.002
[25]	孟波, 孙小巍, 刘凯, 等. 复合材料固化残余应变应变片原位检测方法[J]. 复合材料学报, 2025, 42(1): 560-569. MENG Bo, SUN Xiaowei, LIU Kai, et al. In-situ testing method for residual strain of cured composite materials by strain gauge[J]. Acta Materiae Compositae Sinica, 2025, 42(1): 560-569. (in Chinese MENG Bo, SUN Xiaowei, LIU Kai, et al. In-situ testing method for residual strain of cured composite materials by strain gauge[J]. Acta Materiae Compositae Sinica, 2025, 42(1): 560-569. (in Chinese)