复合材料胶粘修复界面的载荷传递仿真优化
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摘要
胶接修复工艺是飞机结构修理的重要工艺之一,为了研究胶黏工艺对修复效果的影响规律,探索最佳的工艺参数,本文建立胶粘修复的三维模型,利用ANSYS Workbench有限元软件对胶粘修复界面载荷传递进行分析,讨论补片材料、补片厚度、胶层剪切模量和胶层厚度对胶接修复的影响。仿真结果证明补片材料为硼/环氧树脂时,胶粘失效风险最小;补片较厚时,胶接修复效果好,但补片过厚会削弱胶接修复的效果;胶黏剂剪切模量越大越有助于损伤区域的修复,工程应用中建议选用剪切模量较高的胶黏剂;胶层较厚时会增大胶层发生缺陷的概率从而减弱修复效果,建议合理选取厚度较小的胶层。最后提出修复界面的表面处理、复合材料端部的溢胶以及倒角处理均有益于修复结构的载荷传递,缓和胶粘界面应力水平,降低胶层失效的风险。
Composite bonding repair was one of the important processes for aircraft structural repair and the scientific bonding process design was an important factor to ensure the repair effect of aircraft damage structure. In order to study the influence of adhesive technology on repair and explore the best bonding process parameters,the finite element model was established to analyze the load transfer behavior of composite bonding repair interface by ANSYS workbench. The material and thickness of the patch,shear modulus and thickness of adhesive layer were taken to discuss the effect on bonding repair. The simulation results show that when the patch material is boron epoxy resin,the risk of adhesive failure is the smallest. When the patch is thicker,the effect of bonding repair is good,but too thick patch will weaken the effect of bonding repair. The larger shear modulus of the adhesive,the better the repairing of the damaged area. It is suggested to choose adhesive with high shear modulus in engineering application.The thicker layer will increase the probability of defects in the layer so as to weaken the repair effect. Therefore it is suggested to select the layer with minimum thickness reasonably. At last,the surface treatment of the repair interface,the glue overflow at the end of the composite material and the chamfering treatment are all beneficial to the load transfer of the repaired structure,to ease the stress of the adhesive interface and to reduce the risk of layer failure.
Composite bonding repair was one of the important processes for aircraft structural repair and the scientific bonding process design was an important factor to ensure the repair effect of aircraft damage structure. In order to study the influence of adhesive technology on repair and explore the best bonding process parameters,the finite element model was established to analyze the load transfer behavior of composite bonding repair interface by ANSYS workbench. The material and thickness of the patch,shear modulus and thickness of adhesive layer were taken to discuss the effect on bonding repair. The simulation results show that when the patch material is boron epoxy resin,the risk of adhesive failure is the smallest. When the patch is thicker,the effect of bonding repair is good,but too thick patch will weaken the effect of bonding repair. The larger shear modulus of the adhesive,the better the repairing of the damaged area. It is suggested to choose adhesive with high shear modulus in engineering application.The thicker layer will increase the probability of defects in the layer so as to weaken the repair effect. Therefore it is suggested to select the layer with minimum thickness reasonably. At last,the surface treatment of the repair interface,the glue overflow at the end of the composite material and the chamfering treatment are all beneficial to the load transfer of the repaired structure,to ease the stress of the adhesive interface and to reduce the risk of layer failure.
引文
[1]童谷生,孙良新,刘英卫.飞机结构损伤的复合材料胶接修补技术研究进展[J].宇航材料工艺,2002,32(5):20-24+29.
[2]王必宁.复合材料胶接修补金属裂纹板的计算与实验研究[D].西安:西北工业大学,2004.
[3]陈绍杰.用复合材料技术修理金属飞机结构的修理记实[J].航空维修与工程,2000(1):21-22.
[4]程起有,姚磊江,童小燕,等.补片尺寸对复合材料胶接修理性能的影响[J].飞机设计,2004(3):31-33.
[5]赵培仲,黄旭仁,李艳丽,等.补片尺寸对胶层应力分布的影响[J].玻璃钢/复合材料,2012(6):18-22.
[6]代永朝.基于有限元法的飞机蒙皮裂纹加强补片优化设计[J].新技术新工艺,2014(11):34-36.
[7]卢志国,杨纥,林建平.胶层尺寸对单搭胶接接头性能的影响研究[J].中国胶粘剂,2009,18(05):1-3.
[8]张移山,华庆祥.复合材料补片参数对裂纹尖端应力强度因子的影响[J].机械强度,2004(S1):100-103.
[9]杨孚标,肖加余,江大志,等.复合材料单面胶接修复含中心裂纹铝合金板的疲劳特性分析[J].国防科技大学学报,2007,29(3):16-21.
[10]JONES R,CALLINAN R J. Finite element analysis of patched cracks[J]. Journal of Structural Mechanics,2007,7(2):107-130.
[11]陈绍杰.复合材料结构修理指南[M].北京:航空工业出版社,2001.
[12] CHANDRA R, GURUPRASAD K. Numerical estimation of stress intensity factors in patched cracked plates[J]. Engineering Fracture Mechanics,1987,27(5):559-569.
[13]余周辉,赵培仲,胡芳友. CFRP加固修复铝板结构的载荷传递效果[J].航空材料学报,2018,38(1):60-68.
[14]张术宽. FRP加固含缺陷钢结构的破坏力学分析[D].广州:华南理工大学,2013.
[15]杨孚标,肖加余,江大志,等.炭纤维/环氧复合材料单面修补中心裂纹铝合金板的静态和疲劳特性[J].复合材料学报,2007,24(3):1-6.
[16]TOUNSI A,DAOUADJI T H,BENYOUCEF S,et al.Interfacial stresses in FRP-plated RC beams:Effect of adherend shear deformations[J]. International Journal of Adhesion&Adhesives,2009,29(4):343-351.
[17]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(1):18-21.
[18]舒茂盛.飞机壁板战伤修补方法的数值研究[D].西安:西北工业大学,2005.
[19]黄凌凯,章向明,王安稳.复合材料单面加固修补钢板的界面应力分析[J].中国修船,2017,30(6):43-47.
[20]苏维国,穆志韬,王朔.金属裂纹板复合材料胶接修补结构裂纹扩展行为研究[J].沈阳航空航天大学学报,2014,31(1):37-40.
[21]赵立涛,王志瑾.复合材料胶接修补金属裂纹板的应力强度因子研究[J].飞机设计,2011,31(2):67-70.
[22]李煊,党嘉立,郭秉仪.复合材料混合连接接头强度影响因素初探[C].合肥:第十一届全国复合材料学术会议. 2000.
[23]郑小玲,孔凡荣,游敏,等.胶层厚度对拉伸试样应力分布影响的数值分析[J].粘接,2004,25(5):30-32.
[24]邓军,黄培彦.降低CFRP板加固梁界面应力集中方法的研究[J].工业建筑,2007,37(9):109-112.
[25]夏春红.碳纤维布加固钢筋混凝土梁抗弯性能研究[D].上海:同济大学,2002.
[26] TENG J G,ZHANG J W,SMITH S T. Interfacial stresses in reinforced concrete beams bonded with a soffit plate:a finite element study[J]. Construction&Building Materials,2002,16(1):1-14.
[2]王必宁.复合材料胶接修补金属裂纹板的计算与实验研究[D].西安:西北工业大学,2004.
[3]陈绍杰.用复合材料技术修理金属飞机结构的修理记实[J].航空维修与工程,2000(1):21-22.
[4]程起有,姚磊江,童小燕,等.补片尺寸对复合材料胶接修理性能的影响[J].飞机设计,2004(3):31-33.
[5]赵培仲,黄旭仁,李艳丽,等.补片尺寸对胶层应力分布的影响[J].玻璃钢/复合材料,2012(6):18-22.
[6]代永朝.基于有限元法的飞机蒙皮裂纹加强补片优化设计[J].新技术新工艺,2014(11):34-36.
[7]卢志国,杨纥,林建平.胶层尺寸对单搭胶接接头性能的影响研究[J].中国胶粘剂,2009,18(05):1-3.
[8]张移山,华庆祥.复合材料补片参数对裂纹尖端应力强度因子的影响[J].机械强度,2004(S1):100-103.
[9]杨孚标,肖加余,江大志,等.复合材料单面胶接修复含中心裂纹铝合金板的疲劳特性分析[J].国防科技大学学报,2007,29(3):16-21.
[10]JONES R,CALLINAN R J. Finite element analysis of patched cracks[J]. Journal of Structural Mechanics,2007,7(2):107-130.
[11]陈绍杰.复合材料结构修理指南[M].北京:航空工业出版社,2001.
[12] CHANDRA R, GURUPRASAD K. Numerical estimation of stress intensity factors in patched cracked plates[J]. Engineering Fracture Mechanics,1987,27(5):559-569.
[13]余周辉,赵培仲,胡芳友. CFRP加固修复铝板结构的载荷传递效果[J].航空材料学报,2018,38(1):60-68.
[14]张术宽. FRP加固含缺陷钢结构的破坏力学分析[D].广州:华南理工大学,2013.
[15]杨孚标,肖加余,江大志,等.炭纤维/环氧复合材料单面修补中心裂纹铝合金板的静态和疲劳特性[J].复合材料学报,2007,24(3):1-6.
[16]TOUNSI A,DAOUADJI T H,BENYOUCEF S,et al.Interfacial stresses in FRP-plated RC beams:Effect of adherend shear deformations[J]. International Journal of Adhesion&Adhesives,2009,29(4):343-351.
[17]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(1):18-21.
[18]舒茂盛.飞机壁板战伤修补方法的数值研究[D].西安:西北工业大学,2005.
[19]黄凌凯,章向明,王安稳.复合材料单面加固修补钢板的界面应力分析[J].中国修船,2017,30(6):43-47.
[20]苏维国,穆志韬,王朔.金属裂纹板复合材料胶接修补结构裂纹扩展行为研究[J].沈阳航空航天大学学报,2014,31(1):37-40.
[21]赵立涛,王志瑾.复合材料胶接修补金属裂纹板的应力强度因子研究[J].飞机设计,2011,31(2):67-70.
[22]李煊,党嘉立,郭秉仪.复合材料混合连接接头强度影响因素初探[C].合肥:第十一届全国复合材料学术会议. 2000.
[23]郑小玲,孔凡荣,游敏,等.胶层厚度对拉伸试样应力分布影响的数值分析[J].粘接,2004,25(5):30-32.
[24]邓军,黄培彦.降低CFRP板加固梁界面应力集中方法的研究[J].工业建筑,2007,37(9):109-112.
[25]夏春红.碳纤维布加固钢筋混凝土梁抗弯性能研究[D].上海:同济大学,2002.
[26] TENG J G,ZHANG J W,SMITH S T. Interfacial stresses in reinforced concrete beams bonded with a soffit plate:a finite element study[J]. Construction&Building Materials,2002,16(1):1-14.
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