复合材料胶接修复金属构件残余热应力研究进展
Advances in Research of Thermal Residual Stresses in Bonded Composite Repairs of Metallic Components
摘 要
复合材料补片胶接技术是一种有效修复飞机受损构件的低成本方法.由于补片与金属材料热膨胀系数的显著差异,会在构件中引入残余热应力.归纳了复合材料修复技术中关于残余热应力的研究热点及成果,涉及常用的残余热应力分析模型、结构约束及固化制度对残余热应力的影响、减小残余热应力的途径等,并对今后的研究工作进行了展望.
复合材料补片
金属构件
胶接修复
thermal residual stress
composite patch
metallic component
bonded repair
Abstract
Composite patching has been proven to be an efficient and economical method to repair damaged aircraft components.The significant difference in thermal expansion coefficients between the composite patch and the metallic substrate would introduce thermal residual stresses in the components.Research achievements of the thermal residual stresses in composite repairs of metallic components are reviewed,including some widely used models to predict thermal residual stresses,influences of restraint by the surrounding structure and curing cycles on the thermal residual stresses,and methods to minimize the residual stresses.Some recommendations for future work are also presented.
中图分类号 V267
所属栏目
基金项目 武器装备预研基金资助项目(51489040105KG0101)
收稿日期 2006/6/8
修改稿日期 2006/8/29
网络出版日期
作者单位点击查看
备注王遵(1980-),男,山东济宁人,博士研究生.
引用该论文: WANG Zun,XIAO Jia-yu,ZENG Jing-cheng,YANG Fu-biao. Advances in Research of Thermal Residual Stresses in Bonded Composite Repairs of Metallic Components[J]. Materials for mechancial engineering, 2007, 31(4): 5～8
王遵,肖加余,曾竟成,杨孚标. 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
被引情况:
【1】余海洲,赵迪,李阳, "胶瘤入射角度对单搭胶接接头拉剪强度和应力分布的影响",机械工程材料 40, 60-63(2016)
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参考文献
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【6】Baker A A,Jones R.Bonded repair of aircraft structures[M].Dordrecht:Martinus Nijhoff,1988:122-131.
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【13】Naboulsi S,Mall S.Thermal effects on adhesively bonded composite repair of cracked aluminum panels[J].Theoretical & Applied Fracture Mechanics,1997,26:1-12.
【14】Baker A A,Hawkes G A,Lumley E J.Thermal-stress and thermal-fatigue studies[C]//Proceedings of the 2nd International Conference on Composite Materials.Toronto:Metallurgical Society of AIME,1978.
【15】Findik F,Mrad N,Johnson.Strain monitoring in composite patched structures[J].Composite Structures,2000,49:331-338.
【16】Findik F,Unal H.Development of thermal residual strains in a single sided composite patch[J].Composites:Part B,2001,32:379-383.
【17】Djokic D,Johnston A,Rogers A,et al.Residual stress development during the composite patch bonding process:measurement and modeling[J].Composites:Part A,2002,33:277-288.
【18】Rose L R F.A cracked plate repaired by bonded reinforcements[J].International Journal of Fracture,1982,18:135-144.
【19】Jones R,Callinan R J.Thermal considerations in the patching of metal sheets with composites overlays[J].Journal of Structural Mechanics,1980,8(2):143-149.
【20】Baker A A.Fibre composite repair of cracked metallic aircraft components-practical and basic aspects[J].Composites,1987,18(4):293-307.
【21】Sun C T,Caruthers J M.Modeling and lowering residual stresses in bonded composite patch repairs of metallic aircraft structures[R].AFRL-SR-BL-TR-01-0502,2001.
【22】Cho J,Sun C T.Multi-step bonding cycles for lowering thermal residual stresses in composite patch repairs[C]//The 43rd AIAA/ASME/ASCE/AHS/ASC Structures,Structural Dynamics,& Materials Conference.Denver:AIAA,2002.
【23】Bower D I.An introduction to polymer physics[M].Cambridge:Cambridge University Press,2002:193-197.
【24】Timoshenko S.Strength of materials[M].Berkshire:Van Nostrand Reinhold Company,1958:217-221.
【25】Baker A A,Davis M J,Hawkes G A.Repair of fatigue-cracked aircraft structures with advanced fiber composites:residual stress and thermal fatigue studies[C]//Proceedings of the 10th Committee on Aeronautical Fatigue Symposium.Brussels:ICAF,1979.
【2】Baker A A,Callinan R J,Davis M J,et al.Repair of Mirage Ⅲ aircraft using BFRP crack patching technique[J].Theoretical & Applied Fracture Mechanics,1984,2:1-16.
【3】Baker A A,Rose L R F,Walker K F,et al.Repair substantiation for a bonded composite repair to F-111 lower wing skin[J].Applied Composite Materials,1999,6:251-267.
【4】Jones R,Molent L.Application of constitutive modeling and advanced repair technology to F-111C aircraft[J].Composite Structures,2004,66:145-157.
【5】徐建新.复合材料补片胶接修理技术的研究进展[J].航空学报,1999,20(4):381-383.
【6】Baker A A,Jones R.Bonded repair of aircraft structures[M].Dordrecht:Martinus Nijhoff,1988:122-131.
【7】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 & Structures,2000,37(33):4577-4599.
【8】Fredell R S.Damage tolerant repair techniques for pressurized aircraft fuselages[D].Delft:University of Technology,1994.
【9】Baker A A,Jones R.Bonded repair of aircraft structures[M].Dordrecht:Martinus Nijhoff,1988:90-92.
【10】Daverschot D R,Vlot A,Woerden H J M.Thermal residual stresses in bonded repairs[J].Applied Composite Materials,2002,9:179-197.
【11】Albat A M.Thermal residual stresses in boned composite repairs on cracked metal structures[D].Vancouver:The University of British Columbia,1998.
【12】Klug J C,Sun C T.Large deflection effects of cracked aluminum plates repaired with bonded composite patches[J].Composite Structures,1998,42:291-296.
【13】Naboulsi S,Mall S.Thermal effects on adhesively bonded composite repair of cracked aluminum panels[J].Theoretical & Applied Fracture Mechanics,1997,26:1-12.
【14】Baker A A,Hawkes G A,Lumley E J.Thermal-stress and thermal-fatigue studies[C]//Proceedings of the 2nd International Conference on Composite Materials.Toronto:Metallurgical Society of AIME,1978.
【15】Findik F,Mrad N,Johnson.Strain monitoring in composite patched structures[J].Composite Structures,2000,49:331-338.
【16】Findik F,Unal H.Development of thermal residual strains in a single sided composite patch[J].Composites:Part B,2001,32:379-383.
【17】Djokic D,Johnston A,Rogers A,et al.Residual stress development during the composite patch bonding process:measurement and modeling[J].Composites:Part A,2002,33:277-288.
【18】Rose L R F.A cracked plate repaired by bonded reinforcements[J].International Journal of Fracture,1982,18:135-144.
【19】Jones R,Callinan R J.Thermal considerations in the patching of metal sheets with composites overlays[J].Journal of Structural Mechanics,1980,8(2):143-149.
【20】Baker A A.Fibre composite repair of cracked metallic aircraft components-practical and basic aspects[J].Composites,1987,18(4):293-307.
【21】Sun C T,Caruthers J M.Modeling and lowering residual stresses in bonded composite patch repairs of metallic aircraft structures[R].AFRL-SR-BL-TR-01-0502,2001.
【22】Cho J,Sun C T.Multi-step bonding cycles for lowering thermal residual stresses in composite patch repairs[C]//The 43rd AIAA/ASME/ASCE/AHS/ASC Structures,Structural Dynamics,& Materials Conference.Denver:AIAA,2002.
【23】Bower D I.An introduction to polymer physics[M].Cambridge:Cambridge University Press,2002:193-197.
【24】Timoshenko S.Strength of materials[M].Berkshire:Van Nostrand Reinhold Company,1958:217-221.
【25】Baker A A,Davis M J,Hawkes G A.Repair of fatigue-cracked aircraft structures with advanced fiber composites:residual stress and thermal fatigue studies[C]//Proceedings of the 10th Committee on Aeronautical Fatigue Symposium.Brussels:ICAF,1979.
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