飞机螺栓连接件制造偏差的应力集中及处理方法分析（英文）
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摘要
飞机零部件在制造过程中会不可避免的出现偏差。通过分析孔位置偏差对螺栓连接件结构应力的影响,研究了不同边距下的多销荷载分布,得到了详细的应力分布和集中情况。在此基础上,结合超孔直径和堵孔材料厚度两个因素,分析了堵孔加工方法对应力集中的影响规律。这为利用公称应力法确定孔位置偏差零件应力集中引起的疲劳损伤的第一个位置以及用公称应力法估算孔位置偏差零件的疲劳寿命提供了基础数据支持。
Deviation of aircraft parts is inevitable in the manufacturing process. By analyzing the influences of position deviation of holes on structural stress of bolted joints,this research studied multi-pin load distribution under different edge margins and obtained detailed stress distribution and concentration. Furthermore,the influence laws of processing method of plugging holes on stress concentration were analyzed based on the two factors,i. e. the diameter of extra holes and the thickness of hole-plugging materials. This provides basic data supports for determining the first position of fatigue damages caused by stress concentration occurring on parts with position deviation of holes and estimating fatigue life of parts with position deviation of holes by using nominal stress method.
Deviation of aircraft parts is inevitable in the manufacturing process. By analyzing the influences of position deviation of holes on structural stress of bolted joints,this research studied multi-pin load distribution under different edge margins and obtained detailed stress distribution and concentration. Furthermore,the influence laws of processing method of plugging holes on stress concentration were analyzed based on the two factors,i. e. the diameter of extra holes and the thickness of hole-plugging materials. This provides basic data supports for determining the first position of fatigue damages caused by stress concentration occurring on parts with position deviation of holes and estimating fatigue life of parts with position deviation of holes by using nominal stress method.
引文
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[9]LAWLOR V P,MCCARTHY M A,STANLEY W F.An experimental study of bolt-hole clearance effects in double-lap,multi-bolt composite joints[J].Composite Structures,2005,71(2):176-190.
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[12]STARIKOV R,SCHN J.Experimental study on fatigue resistance of composite joints with protruding-head bolts[J].Composite Structures,2002,55(1):1-11.
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[14]CHEN W,LI M H,ZHOU T,et al.Research of aircraft fuselage joining and positioning scheme based on digital assembly variation modeling[J].Machinery Design&Manufacture,2012(1):245-247.
[2]LIU X D,LI Y Z.SHU H,et al.Research method of pin load distribution characteristics of multi-pin joints[J].Acta Materiae Compositae Sinica,2013,30(1):210-217.
[3]ZHU H.Stress field intensity method for analyzing fatigue life of extrusion hole joints[D].Nanjing:Nanjing University of Aeronautics and Astronautics,2014.
[4]YANG H B.Research on detailed stress analysis and optimization design of aircraft joints[D].Xi’an:Northwestern Polytechnical University,2007.
[5]NIU C Y.Stress Analysis and Dimensional Design of Practical Aircraft Structure[M].Beijing:Aviation Industry Press,2009.
[6]GASSON P C.Airframe Stress Analysis and Sizing a Second edition.Niu,M.C.Y.Distributed by Adaso/Adastra Engineering Center,PO Box 3552,Granada Hills,CA 91394,USA.2001.795pp.Illustrated.MYM75 plus postage/packing.ISBN 962-7128-0802[J].Aeronautical Journal,2016,106(1055):50.
[7]EGAN B,MCCARTHY C T,MCCARTHY M A,et al.Modelling a single-bolt countersunk composite joint using implicit and explicit finite element analysis[J].Computational Materials Science,2012,64:203-208.
[8]ZHOU Y,NEZHAD H Y,HOU C,et al.A three dimensional implicit finite element damage model and its application to single-lap multi-bolt composite joints with variable clearance[J].Composite Structures,2015,131:1060-1072.
[9]LAWLOR V P,MCCARTHY M A,STANLEY W F.An experimental study of bolt-hole clearance effects in double-lap,multi-bolt composite joints[J].Composite Structures,2005,71(2):176-190.
[10]EGAN B,MCCARTHY C T,MCCARTHY M A,et al.Modelling a single-bolt countersunk composite joint using implicit and explicit finite element analysis[J].Computational Materials Science,2012,64:203-208.
[11]CHEN W H,LEE S S,YEH J T.Three-dimensional contact stress analysis of a composite laminate with bolted joint[J].Composite Structures,1995,30(3):287-297.
[12]STARIKOV R,SCHN J.Experimental study on fatigue resistance of composite joints with protruding-head bolts[J].Composite Structures,2002,55(1):1-11.
[13]LIU G,HUAN H,KE Y.Study on analysis and prediction of riveting assembly variation of aircraft fuselage panel[J].The International Journal of Advanced Manufacturing Technology,2014,75(5):991-1003.
[14]CHEN W,LI M H,ZHOU T,et al.Research of aircraft fuselage joining and positioning scheme based on digital assembly variation modeling[J].Machinery Design&Manufacture,2012(1):245-247.