基于三维Puck失效准则及唯象模量退化的复合材料臂杆屈曲分析
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摘要
针对碳纤维增强树脂基复合材料(CFRP)臂杆结构在压缩和扭转载荷条件下屈曲与后屈曲问题,采用三维Puck失效准则和基于唯象分析的模量退化方法,同时考虑层合结构就位效应及沿纤维方向应力对横向强度的影响,建立了一种适用于考虑渐进失效CFRP结构的屈曲分析方法,并通过编写有限元软件ANSYS的USERMAT子程序进行了数值实现。与文献中实验结果的对比表明,上述方法能够分析复合材料结构的渐进失效过程和后屈曲承载特性,预测精度高。进而采用此方法,详细分析了某航天器臂杆结构在承受压缩与扭转载荷条件下的屈曲载荷及后屈曲特性。
The buckling and post-buckling analyses of carbon fiber reinforced epoxy-matrix composite(CFRP)arm under compressive and torsional loading conditions were addressed based on three-dimensional Puck failure criterion and phenomenological modulus degradation method.Taking into account the in-situ effect of the laminated structure and the effect of stress along the fiber direction on the transverse strength,a buckling analysis method considering progressive failure process of CFRP structures was established.The numerical implementation was realized by ANSYS material subroutine USERMAT.It is verified by comparing with the experimental results in the literature that,the new method can analyze the progressive failure process and post-buckling behavior of the composite structures with high accuracy.Furthermore,this method was used to analyze the buckling load and post-buckling behavior of a spacecraft composite arm under compressive and torsional loads.
The buckling and post-buckling analyses of carbon fiber reinforced epoxy-matrix composite(CFRP)arm under compressive and torsional loading conditions were addressed based on three-dimensional Puck failure criterion and phenomenological modulus degradation method.Taking into account the in-situ effect of the laminated structure and the effect of stress along the fiber direction on the transverse strength,a buckling analysis method considering progressive failure process of CFRP structures was established.The numerical implementation was realized by ANSYS material subroutine USERMAT.It is verified by comparing with the experimental results in the literature that,the new method can analyze the progressive failure process and post-buckling behavior of the composite structures with high accuracy.Furthermore,this method was used to analyze the buckling load and post-buckling behavior of a spacecraft composite arm under compressive and torsional loads.
引文
[1]谭翔飞,何宇廷,冯宇,等.航空碳纤维树脂基复合材料加筋板压缩屈曲及后屈曲性能[J].航空动力学报,2016,31(10):2359-2369.TAN Xiangfei,HE Yuting,FENG Yu,et al.Buckling and post-buckling performance of aeronautic carbon fiber reinforced resin composite stiffened panel under compression[J].Journal of Aerospace Power,2016,31(10):2359-2369(in Chinese).
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[4] FAROOQ U,MYLER P.Finite element simulation of buckling-induced failure of carbon fibre-reinforced laminated composite panels embedded with damage zones[J].Acta Astronautica,2015,115:314-329.
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[12]张强,洪明.损伤引起加筋板结构屈曲性态变异研究[J].中国舰船研究,2007,2(1):24-29.ZHANG Qiang,HONG Ming.Dynamic stability characteristics of damaged stiffed plates[J].Chinese Journal of Ship Research,2007,2(1):24-29(in Chinese).
[13]张国凡,孙侠生,孙中雷.考虑后屈曲的复合材料加筋壁板承载能力分析[J].航空计算技术,2015,45(5):20-23.ZHANG Guofan,SUN Xiasheng,SUN Zhonglei.Load carrying capacity analysis of stiffened composite panel considering post-buckling[J].Aeronautical Computing Technique,2015,45(5):20-23(in Chinese).
[14]吴义韬,姚卫星,吴富强.复合材料层合板面内渐进损伤分析的CDM模型[J].力学学报,2014,46(1):94-104.WU Yitao,YAO Weixing,WU Fuqiang.CDM model for intralaminar progressive damage analysis of composite laminates[J]. Chinese Journal of Theoretical and Applied Mechanics,2014,46(1):94-104(in Chinese).
[15] DAVILA C G,CAMANHO P P,ROSE C A.Failure criteria for FRP laminates[J].Journal of Composite Materials,2005,39(4):323-345.
[16] PUCK A,SCHURMANN H.Failure analysis of FRP laminates by means of physically based phenomenological models[J].Composites Science and Technology,1998,58(7):1045-1067.
[17] PUCK A,SCHURMANN H.Failure analysis of FRP laminates by means of physically based phenomenological models[J].Composites Science and Technology,2002,62(12-13):1633-1662.
[18] CHANG F K,LESSARD L B.Damage tolerance of laminated composites containing an open hole and subjected to compressive loadings:Part I—Analysis[J].Journal of Composite Materials,1991,25(1):44-64.
[19] DONG H, WANG J,KARIHALOO B L.An improved Puck’s failure theory for fibre-reinforced composite laminates including the in situ,strength effect[J].Composites Science&Technology,2014,98:86-92.
[20] WANG J,KARIHALOO B L.Optimum in situ strength design of laminates under combined mechanical and thermal loads[J].Composite Structures,1999,47(1-4):635-641.
[21] WANG J,KARIHALOO B L.Optimum in situ strength design of composite laminates.Part I:In situ strength parameters[J].Journal of Composite Materials,1996,30(12):1314-1337.
[22] MATTHIAS DEUSCHLE H,KROPLIN B H.Finite element implementation of Puck’s failure theory for fibre-reinforced composites under three-dimensional stress[J].Journal of Composite Materials,2012,46(19-20):2485-2513.
[23] KNOPS M.Analysis of failure in fiber polymer laminates:The theory of alfred puck[M].Berlin:Springer,2008.
[24]沈惠申.板壳后屈曲行为[M].上海:上海科学技术出版社,2013.SHEN Huishen.Postbuckling behavior of plates and shells[M].Shanghai:Shanghai Scientific&Technical Publishers,2013(in Chinese).
[25] WANG J,CALLUS P J,BANNISTER M K.Experimental and numerical investigation of the tension and compression strength of un-notched and notched quasi-isotropic laminates[J].Composite Structures,2004,64(3-4):297-306.
[2]武鹏飞,程小全,张纪奎,等.开口及边界条件对复合材料三分之一柱面壳压缩屈曲性能的影响[J].复合材料学报,2014,31(6):1525-1531.WU Pengfei,CHENG Xiaoquan,ZHANG Jikui,et al.Efeect of opening and boundary condition on compressive buckling properties of composite one-third cylindrical shell[J].Acta Materiae Compositae Sinica,2014,31(6):1525-1531(in Chinese).
[3] NIU M C Y.Composite airframe structures:Practical design information and data[M].1st ed.Hong Kong:Conmilit Press,1992
[4] FAROOQ U,MYLER P.Finite element simulation of buckling-induced failure of carbon fibre-reinforced laminated composite panels embedded with damage zones[J].Acta Astronautica,2015,115:314-329.
[5] NAMDAR,DARENDELILER H.Buckling,postbuckling and progressive failure analyses of composite laminated plates under compressive loading[J].Composites Part B:Engineering,2017,120:143-151.
[6] VESCOVINI R,BISAGNI C.Two-step procedure for fast post-buckling analysis of composite stiffened panels[J].Computers&Structures,2013,128(5):38-47.
[7] XIE D,BIGGERS S B.Postbuckling analysis with progressive damage modeling in tailored laminated plates and shells with a cutout[J].Composite Structures,2003,59(2):199-216.
[8] BONI L,FANTERIA D,LANCIOTTI A.Post-buckling behaviour of flat stiffened composite panels:Experiments vs.analysis[J].Composite Structures,2012,94(12):3421-3433.
[9] CAPUTO F,ESPOSITO R,PERUGINI P,et al.Numerical-experimental investigation on post-buckled stiffened composite panels[J].Composite Structures,2002,55(3):347-357.
[10] HILBURGER M W,STARNES J H.Effects of imperfections on the buckling response of compression-loaded composite shells[J].International Journal of Non-Linear Mechanics,2002,37(4):623-643.
[11]汤国伟,张彤.碟形封头压力容器在内压作用下的弹塑性屈曲及后屈曲行为研究[J].压力容器,2012,29(10):16-22.TANG Guowei,ZHANG Tong.Elastic-plastic buckling and post-buckling of internal pressurized torispherical pressure vessel[J].Pressure Vessel Technology,2012,29(10):16-22(in Chinese).
[12]张强,洪明.损伤引起加筋板结构屈曲性态变异研究[J].中国舰船研究,2007,2(1):24-29.ZHANG Qiang,HONG Ming.Dynamic stability characteristics of damaged stiffed plates[J].Chinese Journal of Ship Research,2007,2(1):24-29(in Chinese).
[13]张国凡,孙侠生,孙中雷.考虑后屈曲的复合材料加筋壁板承载能力分析[J].航空计算技术,2015,45(5):20-23.ZHANG Guofan,SUN Xiasheng,SUN Zhonglei.Load carrying capacity analysis of stiffened composite panel considering post-buckling[J].Aeronautical Computing Technique,2015,45(5):20-23(in Chinese).
[14]吴义韬,姚卫星,吴富强.复合材料层合板面内渐进损伤分析的CDM模型[J].力学学报,2014,46(1):94-104.WU Yitao,YAO Weixing,WU Fuqiang.CDM model for intralaminar progressive damage analysis of composite laminates[J]. Chinese Journal of Theoretical and Applied Mechanics,2014,46(1):94-104(in Chinese).
[15] DAVILA C G,CAMANHO P P,ROSE C A.Failure criteria for FRP laminates[J].Journal of Composite Materials,2005,39(4):323-345.
[16] PUCK A,SCHURMANN H.Failure analysis of FRP laminates by means of physically based phenomenological models[J].Composites Science and Technology,1998,58(7):1045-1067.
[17] PUCK A,SCHURMANN H.Failure analysis of FRP laminates by means of physically based phenomenological models[J].Composites Science and Technology,2002,62(12-13):1633-1662.
[18] CHANG F K,LESSARD L B.Damage tolerance of laminated composites containing an open hole and subjected to compressive loadings:Part I—Analysis[J].Journal of Composite Materials,1991,25(1):44-64.
[19] DONG H, WANG J,KARIHALOO B L.An improved Puck’s failure theory for fibre-reinforced composite laminates including the in situ,strength effect[J].Composites Science&Technology,2014,98:86-92.
[20] WANG J,KARIHALOO B L.Optimum in situ strength design of laminates under combined mechanical and thermal loads[J].Composite Structures,1999,47(1-4):635-641.
[21] WANG J,KARIHALOO B L.Optimum in situ strength design of composite laminates.Part I:In situ strength parameters[J].Journal of Composite Materials,1996,30(12):1314-1337.
[22] MATTHIAS DEUSCHLE H,KROPLIN B H.Finite element implementation of Puck’s failure theory for fibre-reinforced composites under three-dimensional stress[J].Journal of Composite Materials,2012,46(19-20):2485-2513.
[23] KNOPS M.Analysis of failure in fiber polymer laminates:The theory of alfred puck[M].Berlin:Springer,2008.
[24]沈惠申.板壳后屈曲行为[M].上海:上海科学技术出版社,2013.SHEN Huishen.Postbuckling behavior of plates and shells[M].Shanghai:Shanghai Scientific&Technical Publishers,2013(in Chinese).
[25] WANG J,CALLUS P J,BANNISTER M K.Experimental and numerical investigation of the tension and compression strength of un-notched and notched quasi-isotropic laminates[J].Composite Structures,2004,64(3-4):297-306.