机翼盒段连接结构疲劳性能影响因素及有限元分析
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摘要
针对国产某型飞机机翼翼盒典型连接区结构,设计试验件进行疲劳试验,对比分析高锁螺栓不同装配工艺对其疲劳性能的影响。结果表明:对高锁螺栓施加一次拧紧工艺后,再施加适当的二次拧紧力矩,能够有效改善连接结构的疲劳性能。其次,建立连接结构的三维有限元模型,基于正交试验法分别研究螺栓拧紧力矩、板间摩擦系数和螺栓材料弹性模量对基板孔边应力集中系数的影响。研究发现,该3种因素均对孔边应力集中系数有较大影响,其中螺栓拧紧力矩的影响最为显著,表明了适宜的二次定力工艺是提高连接结构疲劳性能的一种有效手段。
Fatigue tests of the specimen designed according to the typical interconnected structures of a certain airplane's wing box were carried out to analyze the effects of different assembly processes of high locked bolts on fatigue performance. The results show that the fatigue performance of interconnected structures can be improved effectively by exerting an appropriate second–tightening torque to high locked bolts after the current assembling processes. A three–dimensional finite element model was established to investigate the effects of tightening torque of bolts, friction coefficient between plates as well as elastic modules of bolts on the stress concentration factor of the hole edge in basic plates.The study indicates that all the three factors have great influence on the stress concentration factor of the hole edge.Furthermore, tightening torque of bolts has the most significant impact. It also shows that exerting a second–tightening torque is an effective mean to improve the fatigue performance of interconnected structures.
Fatigue tests of the specimen designed according to the typical interconnected structures of a certain airplane's wing box were carried out to analyze the effects of different assembly processes of high locked bolts on fatigue performance. The results show that the fatigue performance of interconnected structures can be improved effectively by exerting an appropriate second–tightening torque to high locked bolts after the current assembling processes. A three–dimensional finite element model was established to investigate the effects of tightening torque of bolts, friction coefficient between plates as well as elastic modules of bolts on the stress concentration factor of the hole edge in basic plates.The study indicates that all the three factors have great influence on the stress concentration factor of the hole edge.Furthermore, tightening torque of bolts has the most significant impact. It also shows that exerting a second–tightening torque is an effective mean to improve the fatigue performance of interconnected structures.
引文
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[3]曹增强,王武,杨军.干涉对复合材料机械连接强度的影响[J].航空制造技术,2012,57(12):62-64.CAO Zengqiang,WANG Wu,YANGJun,et al.Effect of interference-fit on failure of composites bolted joint[J].Aeronautical Manufacturing Technology,2012,57(12):62-64.
[4]舒文军,何宇廷,刘仁宇,等.板间摩擦对航空连接件疲劳性能的影响[J].南京航空航天大学学报,2010,42(3):347-350.SHU Wenjun,HE Yuting,LIU Renyu,et al.Friction effects between plates on fatigue performance of aircraft joints[J].Journal of Nanjing University of Aeronautics and Astronautics,2010,42(3):347-350.
[5]魏冉,刘龙权,汪海.复合材料-钛合金多钉连接结构疲劳试验研究[J].机械科学与技术,2012,31(12):1997-2002.WEI Ran,LIU Longquan,WANG Hai.Experimental study of the fatigue performance in multi fasterner composite-to-titanium single lap joints[J].Mechanical Science and Technology for Aerospace Engineering,2012,31(12):1997-2002.
[6]HARTSMITH L J.Bonded-bolted composite joints[J].Journal of Aircraft,2012,22(11):993-1000.
[7]HARTSMITH L J.Design methodology for bonded-bolted composite joints:Technical report AFWAL-TR-81-3154[R].WrightPatterson air Forcebase,Ohio:Flight Dynamics Laboratory/Air Force Wright Aeronautical Laboratories/Air Force Systems Command,1981.
[8]孟毛毛,赵美英,弥晓亮,等.胶-螺混合连接结构强度分析及影响因素研究[J].航空工程进展,2013,4(2):186-192.MENG Maomao,ZHAO Meiying,MI Xiaoliang,et al.Analysis of the bonded-bolted hybrid composite joints’strength and influences[J].Progress in Aeronautical Engineering,2013,4(2):186-192.
[9]KISHI N,AHMED A,YABUKI N,et al.Non-linear finite element analysis of top-and seat-angle with double web-angle connections[J].Structural Engineering&Mechanics,2001,12(2):201-214.
[10]刘兴科,李亚智,刘向东,等.金属和复合材料多钉连接钉载分配研究[J].航空工程进展,2011,2(2):193-196.LIU Xingke,LI Yazhi,LIU Xiangdong,et al.Study on load distribution of multiple-bolted metal to composites joints[J].Progress in Aeronautical Engineering,2011,2(2):193-196.