舰载机壁板剪切后屈曲承载能力预测与试验验证
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摘要
舰载机着舰撞击对机翼盒段产生巨大的扭矩,蒙皮以剪切形式承受扭矩,这是机翼壁板的重要设计工况。为准确预测加筋壁板剪切后屈曲承载能力,采用MSC.NASTRAN软件MRIKS弧长法,将线性屈曲分析的一致模态缺陷位移作为扰动引入后屈曲分析。考虑材料和几何双重非线性,对整体加筋壁板剪切试验件的后屈曲破坏过程进行模拟、对承载能力进行预测。根据剪切试验结果,进行对比分析。结果表明:有限元模拟的加筋板初始屈曲发生在蒙皮上,长桁足够大的相对刚度使得长桁与蒙皮连接线上出现屈曲节点,随着载荷增大,加筋壁板整体"坍塌",与试验现象一致。有限元分析(FEA)得到的初始屈曲载荷与试验结果的误差为1.25%,预测的极限承载载荷与试验破坏载荷的误差为2.4%。表明引入缺陷后的MSC.NASTRAN弧长法非线性后屈曲计算能够准确预测加筋壁板剪切后屈曲承载能力,为加筋壁板剪切试验和强度设计提供了分析方法。
The huge torque,beard by the stiffened panel and caused by the landing impact on the wing box section,is an important condition for the design of wing panels.To accurately predict the shear post-buckling capacity of the stiffened panel,the uniform mode defect displacement of liner bucking analysis is introduced as a disturbance to the post-buckling analysis by using the MSC.NASTRAN MRIKS arc-length method.Considering the geometric and material non-linearity,the post-buckling failure process of the shear specimen of the integrally stiffened panel is simulated and the carrying capability is predicted.Based on the test results,a comparative analysis is carried out,and the results indicate that the initial buckling of the stiffened panel occurs on the skin,and sufficient relative stiffness of the stringer produces the buckling node in the connecting line of the stringer and skin.As the load increases,the stiffened panel collapses,showing consistency with the test phenomenon.Compared with the results of the test,the error of the initial buckling load simulated with Finite Element Analysis(FEA)is about 1.25%,and the error of the failure load predicted with FEA is about 2.4%.So,the nonlinear post-bucking calculation based on the MSC.NASTRAN arc-length method with introduced defect can be used to accurately predict the load bearing capacity of the stiffened panel.The research provides an analytical method for the shear test and strength design of the stiffened panel.
The huge torque,beard by the stiffened panel and caused by the landing impact on the wing box section,is an important condition for the design of wing panels.To accurately predict the shear post-buckling capacity of the stiffened panel,the uniform mode defect displacement of liner bucking analysis is introduced as a disturbance to the post-buckling analysis by using the MSC.NASTRAN MRIKS arc-length method.Considering the geometric and material non-linearity,the post-buckling failure process of the shear specimen of the integrally stiffened panel is simulated and the carrying capability is predicted.Based on the test results,a comparative analysis is carried out,and the results indicate that the initial buckling of the stiffened panel occurs on the skin,and sufficient relative stiffness of the stringer produces the buckling node in the connecting line of the stringer and skin.As the load increases,the stiffened panel collapses,showing consistency with the test phenomenon.Compared with the results of the test,the error of the initial buckling load simulated with Finite Element Analysis(FEA)is about 1.25%,and the error of the failure load predicted with FEA is about 2.4%.So,the nonlinear post-bucking calculation based on the MSC.NASTRAN arc-length method with introduced defect can be used to accurately predict the load bearing capacity of the stiffened panel.The research provides an analytical method for the shear test and strength design of the stiffened panel.
引文
[1]张国凡,孙侠生,孙中雷.复合材料加筋壁板剪切破坏试验与后屈曲分析[J].机械科学与技术,2016,35(8):1280-1285.ZHANG G F,SUN X S,SUN Z L.Failure test and postbuckling analysis of composite stiffened panels under shear load[J].Mechanical Science and Technology for Aerospace Engineering,2016,35(8):1280-1285(in Chinese).
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[9]RICHARD C R,JANACA L J,JOHN B A,et al.Metallic materials properties development and standardization[M].Washington,D.C.:Federal Aviation Administration,2003:3-429.
[10]沈世钊,陈昕.网壳结构稳定性[M].北京:科学出版社,1999.SHEN S Z,CHEN X.Stability of net-shell structure[M].Beijing:Science Publishing,1999(in Chinese).
[11]XU M,SOARES C G.Assessment of the ultimate strength of narrow stiffened panel tests specimens[J].Thin-Walled Structures,2012,55:11-21.
[12]万春华,段世慧,吴存利,等.初始几何缺陷对加筋结构后屈曲分析的影响[J].航空计算技术,2017,47(1):90-93.WAN C H,DUAN S H,WU C L,et al.Influence of initial geometrical imperfection on post-buckling analysis for stiffened structure[J].Aeronautical Computing Technique,2017,47(1):90-93(in Chinese).
[13]陈火红,祁鹏.MSC.Patran/Marc培训教程和实例[M].北京:科学出版社,2004.CHEN H H,QI P.The training tutorial and example about MSC.Patran/Marc[M].Beijing:Science Press,2004(in Chinese).
[14]王勖成.有限单元法[M].北京:清华大学出版社,2003.WANG X C.Finite element method[M].Beijing:Tsinghua University Press,2003(in Chinese).
[2]MALLELA U K,UPADHYAY A.Buckling of laminated composite stiffened panels subjected to in-plane shear:Aparametric study[J].Thin-Walled Structures,2006,44:354-361.
[3]AMBUR D R,JAUNKY N,HILBURGER M W.Progressive failure studies of stiffened panels subjected to shear loading[J].Composite Structures,2004,65(2):129-142.
[4]田伟伟,王峰会,黄建业,等.剪切载荷下加筋板失稳模态的全场数字光学测试[J].应用力学学报,2014,31(6):878-882.TIAN W W,WANG F H,HUANG J Y,et al.Buckling modal of stiffened plate under shear load by full-field numerical optical method[J].Chinese Journal of Applied Mechanics,2014,31(6):878-882(in Chinese).
[5]刘存,赵谋周.加筋壁板面内剪切试验方法分析及试验研究[J].工程与试验,2016,56(2):8-12.LIU C,ZHAO M Z.Analysis and experimental research on test method for in-plane shear of stiffened panel[J].Engineering&Test,2016,56(2):8-12(in Chinese).
[6]王平安,矫桂琼,王波,等.复合材料加筋板在剪切载荷下的屈曲特性研究[J].机械强度,2009,31(1):78-82.WANG P A,JIAO G Q,WANG B,et al.Buckling performance analysis of stiffened composite plate under shear loading[J].Journal of Mechanical Strength,2009,31(1):78-82(in Chinese).
[7]冯宇,何宇廷,邵青,等.复合材料加筋板剪切屈曲特性研究[J].机械强度,2013,35(3):288-291.FENG Y,HE Y T,SHAO Q,et al.Study on shear stability performance of composite stiffened panel[J].Journal of Mechanical Strength,2013,35(3):288-291(in Chinese).
[8]李爱环,支晗.剪切载荷作用下复合材料加筋壁板蒙皮屈曲[J].航空计算技术,2017,47(1):97-100.LI A H,ZHI H.Skin buckling of composite stiffened panel under shear load[J].Aeronautical Computing Technique,2017,47(1):97-100(in Chinese).
[9]RICHARD C R,JANACA L J,JOHN B A,et al.Metallic materials properties development and standardization[M].Washington,D.C.:Federal Aviation Administration,2003:3-429.
[10]沈世钊,陈昕.网壳结构稳定性[M].北京:科学出版社,1999.SHEN S Z,CHEN X.Stability of net-shell structure[M].Beijing:Science Publishing,1999(in Chinese).
[11]XU M,SOARES C G.Assessment of the ultimate strength of narrow stiffened panel tests specimens[J].Thin-Walled Structures,2012,55:11-21.
[12]万春华,段世慧,吴存利,等.初始几何缺陷对加筋结构后屈曲分析的影响[J].航空计算技术,2017,47(1):90-93.WAN C H,DUAN S H,WU C L,et al.Influence of initial geometrical imperfection on post-buckling analysis for stiffened structure[J].Aeronautical Computing Technique,2017,47(1):90-93(in Chinese).
[13]陈火红,祁鹏.MSC.Patran/Marc培训教程和实例[M].北京:科学出版社,2004.CHEN H H,QI P.The training tutorial and example about MSC.Patran/Marc[M].Beijing:Science Press,2004(in Chinese).
[14]王勖成.有限单元法[M].北京:清华大学出版社,2003.WANG X C.Finite element method[M].Beijing:Tsinghua University Press,2003(in Chinese).