CCF300/QY8911层压板破孔损伤快速抢修后的拉伸性能

侯日立; 王春雨; 周平

doi:10.13700/j.bh.1001-5965.2023.0485

CCF300/QY8911层压板破孔损伤快速抢修后的拉伸性能

doi: 10.13700/j.bh.1001-5965.2023.0485

空军工程大学航空机务士官学校，信阳 464000

详细信息

通讯作者:
E-mail：hrl6319@sina.com

中图分类号: V267⁺.4；TB330.1
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出版历程
- 收稿日期: 2023-07-27
- 录用日期: 2023-12-01
- 网络出版日期: 2024-01-05
- 整期出版日期: 2024-07-18

Tensile properties of rapid repaired CCF300/QY8911 laminates with broken hole damage

Aviation Maintenance NCO Academy，Air Force Engineering University，Xinyang 464000，China

More Information

Corresponding author: E-mail：hrl6319@sina.com

摘要

摘要:
针对CCF300/QY8911复合材料层压板破孔损伤抢修后的拉伸强度影响规律和表征方法问题，通过对原始材料标准试件、含预制损伤试件及通过胶接、铆接和胶铆联合修理后试件的拉伸试验，得到了相应的强度、刚度、损伤模式和重点部位应变数据。结果表明，修理部位与原结构刚度不协调是影响修理强度的主要因素；胶接修理具有较高的连接刚度，其修理强度影响因素主要是铺层间结合强度；铆接修理连接刚度较低，且铆钉受单剪容易被拉脱是影响其修理强度的主要因素；胶铆联合修理综合了胶接修理刚度高和铆接修理能防止层间撕裂的双重优势；综合采用胶铆联合湿装配工艺、增加铆钉直径和在工件背面加装防拉脱垫片可显著提高修理效果，其抗拉强度分别为常规铆接修理和常规胶接修理的161.5%和135.9%。所提的基于线弹性断裂理论的强度恢复率评价方法能更好地从整体上表征修理后结构的真实承载能力。
- 层压板 /
- 铆接修理 /
- 胶接修理 /
- 胶铆修理 /
- 单轴拉伸 /
- 拉伸性能
Abstract:
The tensile strength of the CCF300/QY8911 composite laminate after hole damage repair was evaluated using a set of rules and characterization methods. To obtain the necessary data, tensile tests were conducted on standard specimens made from the original material, damaged specimens without repair, and specimens repaired using bonding, riveting, and bonding-riveting joint repair techniques. The corresponding data included strength, stiffness, damage mode, and key point strain. The following conclusions were drawn through comprehensive analysis: the incompatibility between the repair location and the original structure stiffness is the main factor affecting the repair strength; bonding repair has a high connection stiffness, and the main influencing factor of repair strength is the lamina bonding strength;on the other hand, riveting repair, which has a low connection stiffness, is mainly affected by the ease of pulling out the rivet in single shear; bonding-riveting joint repair combines the high stiffness of bonding repair and the dual advantage of riveting repair to prevent interlayer tearing; significantly improving the repair effect by adopting the combined wet assembly process of bonding-riveting, increasing the diameter of rivets, and installing anti-slip pads on the back of the workpiece can achieve a tensile strength of 161.5% and 135.9% higher than the conventional riveting repair and conventional bonding repair, respectively.The method described in this study, which is based on the linear elastic fracture theory, provides a more accurate representation of the real bearing capacity of the restored structure from a comprehensive standpoint.
- laminates /
- riveting repair /
- bonding repair /
- bonding-riveting joint repair /
- uniaxial tension /
- tensile properties

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图 1 热压罐成型工艺曲线

Figure 1. Autoclave process curves

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图 2 含预制损伤的试件

Figure 2. Specimens with prefabricated damage

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图 3 常规铆接修理试件

Figure 3. Specimens repaired by conventional riveting method

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图 4 常规胶接修理试件

Figure 4. Specimens repaired by conventional bonding method

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图 5 改进后的铆接修理试件

Figure 5. Specimens repaired by improved riveting method

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图 6 胶铆联合修理试件

Figure 6. Specimens repaired by adhesive-riveting joint method

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图 7 拉伸实验装置

Figure 7. Tension test equipment

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图 8 标准拉伸实验的断口

Figure 8. Fracture surface of standard tensile test

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图 9 含预制损伤试件的载荷-应变曲线

Figure 9. Load-strain curves of specimens with prefabricated damage

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图 10 含预制损伤试件的载荷-位移曲线

Figure 10. Load-displacement curve of specimens with prefabricated damage

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图 11 含预制损伤试件的断口

Figure 11. Fracture surface of specimens with prefabricated damages

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图 12 常规铆接修理试件的载荷-位移曲线

Figure 12. Load-displacement curves of specimens repaired by simple riveting method

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图 13 不锈钢补片断口

Figure 13. Fracture surface of specimens with stainless steel patch

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图 14 钛合金补片断口

Figure 14. Fracture surface of specimens with titanium alloy patch

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图 15 铆钉受剪变形示意图

Figure 15. Shear deformation schematic of rivet

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图 16 钛合金补片上应变随载荷的变化关系

Figure 16. Relationship between strain and load of titanium alloy patch

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图 17 改进后铆接修理试件的载荷-位移曲线

Figure 17. Load-displacement curves of specimens repaired by improved riveting method

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图 18 改进后铆接修理试件的断口

Figure 18. Fracture surface of specimens repaired by improved riveting method

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图 19 改进后铆接修理试件补片和孔边复合材料的应变

Figure 19. Strain at patch and hole edge composite of specimens repaired by improved riveting method

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图 20 胶接修理试件的载荷-位移曲线

Figure 20. Load-displacement curves of specimens repaired by bonding method

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图 21 胶接修理试件的断口

Figure 21. Fracture surface of specimens repaired by bonding method

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图 22 胶接修理试件补片和孔边复合材料的应变

Figure 22. Strain at patch and hole edge composite of specimens repaired by bonding method

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图 23 胶铆联合修理试件的载荷-位移曲线

Figure 23. Load-displacement curves of specimens repaired by bonding-riveting joint method

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图 24 胶铆联合修理试件的断口

Figure 24. Fracture surface of specimens repaired by bonding-riveting joint method

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图 25 胶铆联合修理试件补片和孔边复合材料的应变

Figure 25. Strain at patch and hole edge composite of specimens repaired by bonding-riveting joint method

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表 1 实验标准及设备

Table 1. Experimental standard and equipment

试件类型	试件数量	实验标准	实验设备
标准拉伸试件	6	ASTM D3039—2017^[20]	电子万能实验机INSTRON 5895 100 kN
含预制损伤的试件	5	ASTM D3039—2017^[20]	电子万能实验机INSTRON 5895 100 kN
不锈钢补片	5	参考ASTM D3039—2017^[20]	电子万能实验机MTS 311 1000 kN
钛合金补片	5	参考ASTM D3039—2017^[20]	电子万能实验机MTS 311 1000 kN

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表 2 材料性能测试结果

Table 2. Experimental results of material properties

试件编号	宽度/ mm	厚度/ mm	载荷/ kN	拉伸强度/MPa	拉伸模量/GPa	破坏应变
1	25.08	1.41	21.4	605	64.7	9216×10⁻⁶
2	25.06	1.40	25.3	721	63.8	11036×10⁻⁶
3	25.09	1.44	23.7	655	65.2	9944×10⁻⁶
4	25.07	1.42	23.4	656	63.6	10333×10⁻⁶
5	25.06	1.38	24.4	705	65.1	10686×10⁻⁶
6	25.04	1.41	23.5	665	64.4	10173×10⁻⁶

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表 3 含预制损伤试件的拉伸性能测试结果

Table 3. Tensile properties results of specimens with prefabricated damage

试样编号	宽度/ mm	厚度/ mm	载荷峰值/kN	拉伸强度/MPa	破坏应变（孔长轴侧）
1	97.66	1.50	21.6	147	4378×10⁻⁶
2	97.78	1.49	21.1	145	4387×10⁻⁶
3	98.18	1.48	20.1	138	3815×10⁻⁶
4	97.77	1.50	19.6	134	3868×10⁻⁶
5	97.83	1.50	21.1	144	4245×10⁻⁶

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表 4 常规铆接修理试件的拉伸性能测试结果

Table 4. Tensile properties results of specimens repaired by simple riveting method

试件形式	试件编号	宽度/mm	厚度/mm	载荷峰值 Ⅰ / kN	拉伸强度 Ⅰ / MPa	载荷峰值 Ⅱ / kN	拉伸强度 Ⅱ / MPa	破坏应变（孔长轴侧）	破坏应变（金属侧）
不锈钢补片	1	98.08	1.48	33.7	232	31.9	220	4326×10⁻⁶	122×10⁻⁶
	2	97.90	1.51	33.7	228	32.8	222	4211×10⁻⁶	68.3×10⁻⁶
	3	98.08	1.44	32.4	229	29.2	207	4256×10⁻⁶	82.6×10⁻⁶
	4	97.97	1.51	35.0	237	32.1	217	4230×10⁻⁶	135×10⁻⁶
	5	98.26	1.45	36.1	253	30.2	212	4469×10⁻⁶	121×10⁻⁶
钛合金补片	1	98.49	1.50	35.3	239	31.9	216	4386×10⁻⁶	259×10⁻⁶
	2	98.28	1.49	33.0	225	30.7	210	4190×10⁻⁶	260×10⁻⁶
	3	98.03	1.41	35.3	256	30.4	220	4423×10⁻⁶	331×10⁻⁶
	4	98.39	1.48	33.6	231	32.5	224	3995×10⁻⁶	240×10⁻⁶
	5	98.41	1.50	33.7	229	32.5	220	4140×10⁻⁶	259×10⁻⁶

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表 5 改进后铆接修理试件的剩余强度测试结果

Table 5. Residual strength test results of specimens repaired by improved riveting method

试件编号	宽度/mm	厚度/mm	载荷/kN	剩余强度/MPa
1	98.60	1.50	47.90	323.8
2	98.54	1.48	47.53	325.9
3	98.70	1.48	49.62	339.7
4	98.70	1.44	46.44	326.7
5	98.64	1.44	47.99	337.9

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表 6 胶接修理试件的剩余强度测试结果

Table 6. Residual strength test results of specimens repaired by bonding method

试件编号	宽度/mm	厚度/mm	载荷/kN	剩余强度/MPa
1	98.84	1.5	39.47	266.2
2	98.4	1.48	40.41	277.5
3	98.2	1.4	40.82	296.9

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表 7 胶铆联合修理试件的剩余强度测试结果

Table 7. Residual strength test results of specimens repaired by bonding-riveting joint method

试件编号	宽度/mm	厚度/mm	载荷/kN	剩余强度/MPa
1	99.20	1.48	58.20	396.40
2	98.64	1.46	54.75	380.20
3	98.12	1.50	53.88	366.10

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表 8 评价方法改进前后的结构强度恢复率对比

Table 8. Comparison of strength recovery ratio by unimproved and improved evaluation methods

修理方法	修正因子F₂	修复强度/ MPa	强度恢复率（旧）/%	强度恢复率（新）/%
常规铆接修理	0.601	361.9	35.3	54.2
胶接修理	0.505	430.7	41.9	64.5
改进后的铆接修理	0.428	508.1	49.5	76.1
胶铆联合修理	0.372	584.7	57.0	87.6

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参考文献(29)

[1]	魏士礼, 赵艳秦. 民用飞机复合材料翼盒蒙皮损伤外补修理[J]. 机械工程师, 2022(4): 82-84. doi: 10.3969/j.issn.1002-2333.2022.4.jxgcs202204027 WEI S L, ZHAO Y Q. External patch repair for damage of composite wing box skin of civil aircraft[J]. Mechanical Engineer, 2022(4): 82-84(in Chinese). doi: 10.3969/j.issn.1002-2333.2022.4.jxgcs202204027
[2]	刘岩松, 张子健, 宋晓晨, 等. 复合材料结构修理技术探究[J]. 航空维修与工程, 2018(11): 76-80. doi: 10.3969/j.issn.1672-0989.2018.11.029 LIU Y S, ZHANG Z J, SONG X C, et al. Research on repair technology of composite material structure[J]. Aviation Maintenance & Engineering, 2018(11): 76-80(in Chinese). doi: 10.3969/j.issn.1672-0989.2018.11.029
[3]	贺旺, 曹强, 孙涛. 飞机复合材料修理工艺研究的思路探讨[J]. 航空维修与工程, 2016(4): 57-59. HE W, CAO Q, SUN T. Discussion on the process research of aircraft composite repair[J]. Aviation Maintenance & Engineering, 2016(4): 57-59(in Chinese).
[4]	孔磊. 飞机复合材料修理技术研究[J]. 塑料工业, 2019, 47(3): 140-144. doi: 10.3969/j.issn.1005-5770.2019.03.033 KONG L. Research on aircraft composite repair technology[J]. China Plastics Industry, 2019, 47(3): 140-144(in Chinese). doi: 10.3969/j.issn.1005-5770.2019.03.033
[5]	聂恒昌, 谭日明, 郭霞, 等. 复合材料层合板机械连接修理拉伸性能[J]. 北京航空航天大学学报, 2016, 42(2): 318-327. NIE H C, TAN R M, GUO X, et al. Tensile performances of mechanically fastened repairs of composite laminates[J]. Journal of Beijing University of Aeronautics and Astronautics, 2016, 42(2): 318-327(in Chinese).
[6]	杨鹏飞, 樊俊铃, 宁宁, 等. 复合材料矩形开孔损伤螺接修理参数分析[J]. 航空维修与工程, 2021(5): 89-93. doi: 10.3969/j.issn.1672-0989.2021.05.032 YANG P F, FAN J L, NING N, et al. Analysis on repair parameters for damaged bolted joints with rectangular holes in composite materials[J]. Aviation Maintenance & Engineering, 2021(5): 89-93(in Chinese). doi: 10.3969/j.issn.1672-0989.2021.05.032
[7]	王航, 李想, 谢宗蕻, 等. 含通孔损伤复材壁板螺接修理接头拉伸性能试验研究[J]. 航空制造技术, 2018, 61(20): 56-62. WANG H, LI X, XIE Z H, et al. Tests on tensile strength of bolted-repaired composite joints[J]. Aeronautical Manufacturing Technology, 2018, 61(20): 56-62(in Chinese).
[8]	张阿盈, 许洪明, 陈昊. 复合材料层压板铆接修补剩余强度评估[J]. 机械强度, 2016, 38(1): 105-109. ZHANG A Y, XU H M, CHEN H. Residual strength evaluation of composite laminates repaired by riveted metal patch[J]. Journal of Mechanical Strength, 2016, 38(1): 105-109(in Chinese).
[9]	张阿盈, 陈向明, 王力立. 含离散源损伤复合材料加筋板剩余强度及其修理技术研究[J]. 工程与试验, 2018, 58(2): 16-19. doi: 10.3969/j.issn.1674-3407.2018.02.004 ZHANG A Y, CHEN X M, WANG L L. Study on residual strength of composite stiffened panel with discrete source damage and repair technique[J]. Engineering & Test, 2018, 58(2): 16-19(in Chinese). doi: 10.3969/j.issn.1674-3407.2018.02.004
[10]	梁凤飞, 金迪, 何勇. 复合材料结构修理研究[J]. 中国胶粘剂, 2019, 28(5): 57-61. LIANG F F, JIN D, HE Y. Research on the maintenance of composite material structure[J]. China Adhesives, 2019, 28(5): 57-61(in Chinese).
[11]	王锡然. 复合材料机翼结构胶接修理后强度评估模型研究[D]. 天津: 中国民航大学, 2018. WANG X R. Strength evaluation model of composite wing structure after adhesive repair[D]. Tianjin: Civil Aviation University of China, 2018(in Chinese).
[12]	田可可. 复合材料挖补结构性能分析和实验研究[D]. 郑州: 郑州大学, 2021. TIAN K K. Numerical and experimental study on scarf repairment properties of composite material[D]. Zhengzhou: Zhengzhou University, 2021(in Chinese).
[13]	王宇灿. 复合材料胶铆混合修理力学特性实验研究[D]. 天津: 中国民航大学, 2019. WANG Y C. Experimental study on mechanical properties of adhesive-rivet hybrid repair of composite materials[D]. Tianjin: Civil Aviation University of China, 2019(in Chinese).
[14]	张昂. 碳纤维复合材料的激光清洗机理与表面改性研究[D]. 镇江: 江苏大学, 2019. ZHANG A. Research on laser cleaning mechanism and surface modification of carbon fiber reinforced polymer[D]. Zhenjiang: Jiangsu University, 2019(in Chinese).
[15]	李俊磊. 基于激光表面处理的民机复合材料结构胶结修理研究[D]. 广汉: 中国民用航空飞行学院, 2016. LI J L. Civil aircraft composite structure based on laser surface treatment[D]. Guanghan: Civil Aviation Flight University of China, 2016(in Chinese).
[16]	邹维杰. 复合材料层合板机械修理研究[D]. 南京: 南京航空航天大学, 2018. ZOU W J. Research on mechanical repair of composite laminates[D]. Nanjing: Nanjing University of Aeronautics and Astronautics, 2018(in Chinese).
[17]	王瑞峰. 复合材料胶铆混合连接与胶接修理的力学性能对比研究[D]. 天津: 中国民航大学, 2016. WANG R F. A comparative study of mechanical property of bonded repair and adhesive-rivet hybrid repair of composite laminate[D]. Tianjin: Civil Aviation University of China, 2016(in Chinese).
[18]	原志翔. 复合材料胶铆混合修理损伤特性实验研究[D]. 天津: 中国民航大学, 2020. YUAN Z X. Experimental study on damage properties of adhesive-rivet hybrid repair of composite materials[D]. Tianjin: Civil Aviation University of China, 2020(in Chinese).
[19]	徐航. 复合材料胶铆混合修理优化设计[D]. 天津: 中国民航大学, 2015. XU H. Optimal design of composite material adhesive-rivet hybrid repair[D]. Tianjin: Civil Aviation University of China, 2015(in Chinese).
[20]	ASTM. Standard test method for tensile properties of polymer matrix composite materials: ASTM D3039—2017[S]. West Conshohocken: ASTM International, 2017.
[21]	中国飞机强度研究所、中国航空综合技术研究所、中国航空工业第601 研究所,等. 飞机复合材料结构机械连接设计要求: HB 7709[S]. 北京: 国防科学技术工业委员会, 2003. Aircraft Strength Research Institute of China, China Aero-poly Technology Establishment, AVIC Shenyang Aircraft Design & Research Institute, et al. Design requirements of mechanically fastened joint of composite structure for airplane: HB 7099[S]. Beijing: Commission of Science, Technology and Industry for National Defense, 2003(in Chinese).
[22]	USHAKOV A, STEWART A, MISHULIN I. Probabilistic design of damage tolerant composite aircraft structures[R]. Washington, D. C. : US Department of Transportation, 2002.
[23]	王辰, 贺尔铭, 赵志彬, 等. 民机复合材料结构修理容限确定方法研究[J]. 西北工业大学学报, 2020, 38(4): 695-704. doi: 10.3969/j.issn.1000-2758.2020.04.002 WANG C, HE E M, ZHAO Z B, et al. Method for determining repair tolerance of civil aircraft composite structure[J]. Journal of Northwestern Polytechnical University, 2020, 38(4): 695-704(in Chinese). doi: 10.3969/j.issn.1000-2758.2020.04.002
[24]	中国人民解放军空军第一研究所. 飞机战伤评估与修理技术手册编制要求: GJB 3897—99[S]. 北京: 中国人民解放军总装备部, 1999. Air Force First Research Institute of PLA. Requirements for developing technical manuals for aircraft battle damage assessment and repair: GJB 3897—99[S]. Beijing: PLA General Armament Department, 1999(in Chinese).
[25]	FLCMC/HIAM Technical Data Section. Detail specification manuals, technical-aircraft battle damage assessment and repair: MIL-DTL-87158D[S]. Washington, D. C. : US Department of Defense, 2016.
[26]	中国航空研究院. 军用飞机疲劳·损伤容限·耐久性设计手册第三册损伤容限设计[M]. 北京: 中国航空研究院, 1994: 328-335. Chinese Aeronautical Establishment. Fatigue, damage tolerant and durability design for military airplane. Volume Ⅲ. Damage tolerant design[M]. Beijing: Chinese Aeronautical Establishment, 1994: 328-335(in Chinese).
[27]	JOHN G A. Design manual for impact damage tolerant aircraft structure: AGARD-AG-238[R]. Washington, D. C. : AGARD, 1981: 161-168.
[28]	中国航空研究院. 应力强度因子手册(增订版)[M]. 北京: 科学出版社, 1993: 3-9. Chinese Aeronautical Establishment. Stress intensity factors handbook(revised and enlarged edition)[M]. Beijing: Science Press, 1993: 3-9(in Chinese).
[29]	航空航天工业部科学技术研究院. 飞机结构耐久性及损伤容限设计手册第三册飞机结构的损伤容限设计[M]. 北京: 航空航天工业部科学技术研究院, 1989. Academy of Science and Technology Ministry of Aerospace Industry. Durability and damage tolerant design for airplane structure. Volume Ⅲ. Damage tolerant design for airplane structure[M]. Beijing: Academy of Science and Technology Ministry of Aerospace Industry, 1989(in Chinese).