胶接和共固化成型对复合材料加筋板压缩性能的影响
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摘要
为了研究胶接和共固化成型的复合材料加筋板的压缩性能,本文首先开展了两类加筋板轴压试验。然后,建立了渐进损伤有限元模型,模拟加筋板压缩失效过程。复合材料根据Hashin准则判定其失效,蒙皮和筋条间界面采用二次应力准则作为损伤起始判据。通过引入指数形式的损伤状态变量,直接折减材料失效点刚度矩阵来模拟材料的失效过程。随后,根据试验和有限元结果,详细讨论了加筋板的压缩过程。结果表明,两类加筋板失效模式一致,而胶接加筋板比共固化加筋板压缩承载能力略高。
In order to research the compression performance of secondary bonding and co-curing composite stiffened panels,the axial compression tests of two kinds of stiffened panels are carried out in this paper. Then,a progressive damage finite element model is established to simulate the compression failure process of stiffened panels. The failure of the composite is judged according to Hashin criterion. The quadratic stress criterion is adopted as the criterion of damage initiation at the interface between skin and rib. In order to simulate the failure process of material,the stiffness matrix is directly reduced by introducing damage state variables with exponential form at failure point. Afterwards,the compression process of the stiffened panel is discussed in detail according to the experimental results and the finite element results. The results show that the failure modes of the two kinds of stiffened panels are the same,while the compressive strength of secondary bonding stiffened panels is slightly higher than the co-curing stiffened panels.
In order to research the compression performance of secondary bonding and co-curing composite stiffened panels,the axial compression tests of two kinds of stiffened panels are carried out in this paper. Then,a progressive damage finite element model is established to simulate the compression failure process of stiffened panels. The failure of the composite is judged according to Hashin criterion. The quadratic stress criterion is adopted as the criterion of damage initiation at the interface between skin and rib. In order to simulate the failure process of material,the stiffness matrix is directly reduced by introducing damage state variables with exponential form at failure point. Afterwards,the compression process of the stiffened panel is discussed in detail according to the experimental results and the finite element results. The results show that the failure modes of the two kinds of stiffened panels are the same,while the compressive strength of secondary bonding stiffened panels is slightly higher than the co-curing stiffened panels.
引文
[1]陈祥宝.先进树脂基复合材料的发展和应用[J].航空材料学报,2003,23(Z1):198-203.
[2]杜善义,关志东.我国大型客机先进复合材料技术应对策略思考[J].复合材料学报,2008,25(1):1-10.
[3]崔德刚.结构稳定性设计手册[M].北京:航空工业出版社,1996.
[4]常圆圆,许希武,郭树祥.压缩载荷下复合材料整体加筋板渐进损伤非线性数值分析[J].复合材料学报,2010,28(4):201-210.
[5]徐荣章,关志东,王仁宇,等.不同工艺成型复合材料加筋板轴压破坏机理分析[J].北京航空航天大学学报,2016,42(5):1032-1038.
[6]Hashin Z,et al.Failure criteria for unidierctional fiber composites[J].Journal of Applied Mechanics,1980,47:329-334.
[7]王跃全,童明波,朱书华.三维复合材料层合板渐进损伤非线性分析模型[J].复合材料学报,2009,26(5):159-166.
[8]Peter Linde,Jurgen Pleitner,Henk de Boer,et al.Modelling and Simulation of Fibre Metal Laminates[C].2004ABAQUS Users'Conference.Boston Massachusetts:ABAQUS Inc.,2004:421-439.
[9]Camanho,P.P.Dávila,C.G..Mixed-Mode Decohesion Elements for the Simulation of Delamination in Composite Materials[R].NASA,2002,21:17-37.
[10]Krueger,R.,M.K.Cvitkovich,T.K.O'Brien,,et al.Testing and Analysis of Composite Skin/Stringer Debonding under Multi-Axial Loading[J].Journal of Composite Materials,2000,34(15):1263-1300.
[2]杜善义,关志东.我国大型客机先进复合材料技术应对策略思考[J].复合材料学报,2008,25(1):1-10.
[3]崔德刚.结构稳定性设计手册[M].北京:航空工业出版社,1996.
[4]常圆圆,许希武,郭树祥.压缩载荷下复合材料整体加筋板渐进损伤非线性数值分析[J].复合材料学报,2010,28(4):201-210.
[5]徐荣章,关志东,王仁宇,等.不同工艺成型复合材料加筋板轴压破坏机理分析[J].北京航空航天大学学报,2016,42(5):1032-1038.
[6]Hashin Z,et al.Failure criteria for unidierctional fiber composites[J].Journal of Applied Mechanics,1980,47:329-334.
[7]王跃全,童明波,朱书华.三维复合材料层合板渐进损伤非线性分析模型[J].复合材料学报,2009,26(5):159-166.
[8]Peter Linde,Jurgen Pleitner,Henk de Boer,et al.Modelling and Simulation of Fibre Metal Laminates[C].2004ABAQUS Users'Conference.Boston Massachusetts:ABAQUS Inc.,2004:421-439.
[9]Camanho,P.P.Dávila,C.G..Mixed-Mode Decohesion Elements for the Simulation of Delamination in Composite Materials[R].NASA,2002,21:17-37.
[10]Krueger,R.,M.K.Cvitkovich,T.K.O'Brien,,et al.Testing and Analysis of Composite Skin/Stringer Debonding under Multi-Axial Loading[J].Journal of Composite Materials,2000,34(15):1263-1300.