Finite Element Analysis of Carrying Capacity of the Adhesive Bonding Repaired Composite
摘 要
对复合材料损伤构件进行胶接修理, 在MTS试验机上进行拉伸试验, 记录不同修理方式下, 修理构件能够承受的最大载荷; 用Abaqus有限元软件对修理后构件进行强度仿真, 计算损伤修理构件的最大承载能力, 并与试验数据进行对比。结果表明: 有限元分析结果与试验结果吻合较好, 误差小于10%, 证明有限元模型的建立及计算方法符合工程实际要求; 最佳的修补参数为复合材料修理补片纤维方向与母板纤维方向成0°/90°, 补片大小为损伤面积的2~3倍, 补片厚度为损伤深度的0.6~0.75倍。
Abstract
The adhesive bonding repairing technology was used to repair the damage of the composite material components, and the tensile test was carried out on the MTS equipment to record the maximal loads that the components can endure under the different way. The intensity of repaired components was simulated through finite element software of Abaqus to calculate the maximum of load which was compared with the experimental data. The results show that the data of the simulation and experimentation were similar with the deviation less than 10%, which proved that the simulation model and the compute method were up to the mustard of engineering; The best repairing parameters were gained as following: the direction of the repairing patch and motherboard was vertical; the patch was 2-3 times the size of the damage area; the ratio of patch thickness and damage depth was 0.6-0.75.
中图分类号 TB332
所属栏目 物理模拟与数值模拟
基金项目
收稿日期 2011/8/24
修改稿日期 2012/4/19
网络出版日期
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备注向法武(1985-), 男, 湖南溆浦人, 硕士研究生。
引用该论文: XIANG Fa-wu,LI Shu-lin,SHI Xiao-peng,YANG Zhe,ZHANG Tie-jun. Finite Element Analysis of Carrying Capacity of the Adhesive Bonding Repaired Composite[J]. Materials for mechancial engineering, 2012, 36(8): 101~104
向法武,李曙林,石晓鹏,杨哲,张铁军. 损伤复合材料胶接修理后承载能力的有限元分析[J]. 机械工程材料, 2012, 36(8): 101~104
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参考文献
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【2】JONES J S, GRAVES S R.Repair technique for Celion/LARC-160 graphite/polyimide composite structures[M].Washington D C: National Aeronautics and Space Administration, Scientific and Technical Information Branch, 1984.
【3】孟凡颢, 陈绍杰, 董善艳, 等.复合材料损伤结构胶接补强修补分析及设计[J].飞机设计, 2002, 3(1): 18-21.
【4】OKAFOR C A, SINGH N, ENEMUOH U E, et al. Design analysis and performance of adhesively bonded composite patch repair of cracked aluminum aircraft panels[J].Composite Structures, 2005, 71(2):258-270.
【5】OUINASD, HEBBARA, BACHIR, et al. Numerical analysis of the stress intensity factors for repaired cracks from a notch with bonded composite semicircular patch[J].Composites, 2009, 40(6):804-810.
【6】OUDAD W, BOUIADJRA B B, BELHOUARI M, et al. Analysis of the plastic zone size ahead of repaired cracks with bonded composite patch of metallic aircraft structures[J].Computational Materials Science, 2009, 46(5):950-954.
【7】矫桂琼, 贾普荣.复合材料力学[M].西安: 西北工业大学出版社, 2008.
【8】李小慧, 金石磊, 孙斓珲, 等. 聚酯纤维布增强环氧树脂基复合材料的拉伸和摩擦学性能[J].机械工程材料, 2010, 34(3): 61-65.
【9】喻梅, 胡新宇.复合材料挖补修理结构的有限元建模及精度影响分析[J].安徽建筑工业学院学报: 自然科学版, 2009, 17(6):1-6.
【10】程起有, 姚磊江.补片尺寸对复合材料胶接修理性能的影响[J].飞机设计, 2004, 4(3):31-33.
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