飞机焊接加筋壁板拉伸强度预估方法研究
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摘要
对民机焊接加筋壁板结构的拉伸强度预估方法进行研究,依据复合材料力学中弹性模量混合律,提出一个预估飞机壁板结构拉伸强度的理论公式,并通过引入焊接接头的力学性能、离面弯矩、长桁截面形状、蒙皮应力集中等4个系数,反映各因素对壁板结构强度的影响。通过与飞机新型搅拌摩擦焊接铝锂合金壁板拉伸试验结果比较可知,理论计算值比试验值大3. 81%,误差较小,证明了本研究所建立的理论公式具有一定的可靠性和正确性,所述的预估方法可为焊接加筋壁板结构的选材、工艺性能的改进和航天设计人员预估飞机壁板强度值提供参考。此外,利用有限元方法对两组具有不同焊缝状态的壁板的拉伸力学行为进行了模拟分析,结果表明焊接加筋壁板在拉伸破损失效过程中,焊缝开裂状态对壁板抗拉强度无太大影响,同时通过有限元应力云图可以观察到壁板的高应力区,显示壁板的失效过程,在今后对新型民机焊接壁板结构的设计和选材预研阶段,可以通过有限元模拟替代飞机壁板大型结构件拉伸试验,减少预研的周期和成本,提高试验的效率。
This paper studied methods to predict the tensile strength of stiffened-welded plate structure for civil aircraft welding. Based on the law of elastic modulus in the composite material mechanics,a theoretical formula is proposed to estimate the tensile strength of the aircraft welding plate structure,and through the introduction of the mechanical properties of the welded joints,out of plane moment,long truss shape,skin stress concentration four the coefficient,reflecting the influence of factors on the strength of the welded plate structure. The results show that the theoretical calculation is 3. 81% larger than the experimental value,and the error is small,which proves that the theoretical formula established by this study has certain reliability and correctness. The estimation method can provide a reference for the selection of stiffened-welded plate structure material,the improvement of process performance and the aerospace designers ' estimated strength value of aircraft stiffened-welded plate structure. In addition,the tensile mechanical behaviors of two groups of welding plate with different welding states were simulated and analyzed by using the finite element method. The results show that the cracking state of the weld has no great influence on the tensile strength of the stiffened-welded plate,and through the finite element stress cloud can be observed in the welding plate of the high stress area,showing the failure process,in the future for the new civil welding wall structure design and selection of preresearch stage. The finite element simulation is used to replace the tensile test of large structural members of aircraft siding,reduce the cycle and cost of pre-research,and improve the efficiency of the test.
This paper studied methods to predict the tensile strength of stiffened-welded plate structure for civil aircraft welding. Based on the law of elastic modulus in the composite material mechanics,a theoretical formula is proposed to estimate the tensile strength of the aircraft welding plate structure,and through the introduction of the mechanical properties of the welded joints,out of plane moment,long truss shape,skin stress concentration four the coefficient,reflecting the influence of factors on the strength of the welded plate structure. The results show that the theoretical calculation is 3. 81% larger than the experimental value,and the error is small,which proves that the theoretical formula established by this study has certain reliability and correctness. The estimation method can provide a reference for the selection of stiffened-welded plate structure material,the improvement of process performance and the aerospace designers ' estimated strength value of aircraft stiffened-welded plate structure. In addition,the tensile mechanical behaviors of two groups of welding plate with different welding states were simulated and analyzed by using the finite element method. The results show that the cracking state of the weld has no great influence on the tensile strength of the stiffened-welded plate,and through the finite element stress cloud can be observed in the welding plate of the high stress area,showing the failure process,in the future for the new civil welding wall structure design and selection of preresearch stage. The finite element simulation is used to replace the tensile test of large structural members of aircraft siding,reduce the cycle and cost of pre-research,and improve the efficiency of the test.
引文
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[11]熊峻江,刘洪天,寇长河,等.复合材料可靠性设计的小子样系数法[J].复合材料学报,2001(3):112-118.XIONG JunJiang,LIU Hong Tian,KOU ChangHe,et al.Small sample factor method for reliability design of composites[J].Acta Materiae Compositae Sinica,2001(3):112-118(In Chinese).
[12]卓彬,姬书得,王磊,等,焊接技术在大飞机机体研制中的应用及展望[J].航空制造技术,2014(17):50-53.ZHUO Bin,JI ShuDe,WANG Lei,et al.Application and Prospect of Welding Technology in Lage Aircraft Fuselage[J].Aeronautic Manufacturing Technology,2014(17):50-53(In Chinese).
[2]张彦军,李小鹏.2524-T3铆接接头与搅拌摩擦焊接接头疲劳性能对比研究[J].机械强度,2015(03):429-434.ZHANG Yan Jun,LI Xiao Peng.Resersch on fatigue behaviour comparison of aluminum riveted joint and friction stir welding joint[J].Journal of Mechanical Strength,2015(03):429-434(In Chinese).
[3]李亚智.飞机结构疲劳和断裂分析中若干问题的研究[D].西安:西北工业大学,2003:65-68.LI Ya Zhi.Some topics on the fatigue and fracture of aircraft structures[D].Xian:Northwestern Polytechnical University,2003:65-68(In Chinese).
[4]BRIGHTON H,CHRISTOPHER T.Fracture strength evaluation of titanium alloys using modified average stress criterion[J].Transactions of Nonferrous Metals Society of China,2013(23):1072-1079.
[5]TWEEDY B,SELLMEYER S,et al.Static strength comparison of riveted versus friction stir welded stiffened panels[C]//47th AIAA//ASME//ASCE//ASC Structures,tructural Dynamics,and Materials Conference,May 1-4,2006,Newport,Rhode Island.Washington DC:AIAA,2006:1-5.
[6]龙兵,常新龙,方鹏亚等.含裂纹固体推进剂试件抗拉强度的估算[J].火炸药学报,2014,37(2):65-68.LONG Bing,CHANG Xin Long,FANG PengYa et al.Prediction of the tensile strength of solid propellant specimen with crack[J].Chinese Journal of Explosives,2014,37(2):65-68(In Chinese).
[7]孙景峰,郑子樵,林毅,等.2060合金FSW接头微观组织与力学性能[J].中国有色金属学报,2014,24(2):364-370.SUN Jing Feng,ZHENG Zi Qiao,LIN Yi,et al.Microstructures and mechanical properties of 2060 alloy FSW joint[J].Transactions of Nonferrous Metals Society of China,2014,24(2):364-370(In Chinese).
[8]王望,王永军,刘天骄,等.2099和2196铝锂合金挤压型材拉伸性能[J].宇航材料工艺,2014(2):55-59.WANG Wang,WANG Yong Jun,LIU TianJiao,et al.Tensile Properties of 2099 and 2196 Al-Li Alloy Extrusions[J].Aerospace Materials&Technology,2014(2):55-59(In Chinese).
[9]Paulsen F,Welo T.Cross-sectional deformations of rectabgular hollow sections in bending:part I-experiments[J].International Journal of Mechanical Sciences,2001,43(l):109-129.
[10]李令芳.民机结构耐久性与损伤容限设计手册(上册).疲劳设计与分析[M].北京:航空工业出版社,2003.LI Ling Fang.Design of durability and damage tolerance for civil machine structures[M].Beijing:Aviation Industry Press,2003(In Chinese).
[11]熊峻江,刘洪天,寇长河,等.复合材料可靠性设计的小子样系数法[J].复合材料学报,2001(3):112-118.XIONG JunJiang,LIU Hong Tian,KOU ChangHe,et al.Small sample factor method for reliability design of composites[J].Acta Materiae Compositae Sinica,2001(3):112-118(In Chinese).
[12]卓彬,姬书得,王磊,等,焊接技术在大飞机机体研制中的应用及展望[J].航空制造技术,2014(17):50-53.ZHUO Bin,JI ShuDe,WANG Lei,et al.Application and Prospect of Welding Technology in Lage Aircraft Fuselage[J].Aeronautic Manufacturing Technology,2014(17):50-53(In Chinese).