复合材料厚板双轴非线性刚度特性分析

Abstract

Abstract: An incremental solution method based on thick laminate theory coupled with a nonlinear constitutive model is applied to the stiffness analysis of thick composite laminates under biaxial load during progressive failure calculation. The 3D Hashin criterion is employed to predict the failure of the individual plies in the laminates. Degradation is performed when failure is predicted and the stiffness of the laminates is updated step by step during the incremental solution. A program written in PCL (Patran Command Language, the secondary development language of commercial FEM software MSC.Patran) is employed to analyze the nonlinear stress-strain variation for different laminates with various materials. The process of progressive stiffness analysis in this paper provides the foundation for stiffness variation analysis during the failure process of thick composite laminates.

Key words: nonlinear constitutive model, thick laminate theory, stiffness degradation, progressive failure, biaxial load

CLC Number:

V414.8
TB332

WU Chunbo, CHEN Xiuhua, YU Yin, WANG Hai. Nonlinear Stiffness Analysis of Thick Composite Laminate Under Biaxial Load[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2012, 33(7): 1236-1244.

References

[1] Fu X H, Chen H R, Wang Z M. A refined higher-order theory and its finite element method for thick laminated plates. Acta Materiae Compositae Sinica, 1992, 9(2): 39-47. (in Chinese) 傅晓华, 陈浩然, 王震鸣. 复合材料多层厚板的精化高阶理论及其有限元法. 复合材料学报, 1992, 9(2): 39-47.
[2] Huang Z M, Zhang H S. Current status and future trend of researches on the strength of fiber-reinforced composites—a summary of the results from a "failure Olymlics". Advances in Mechannics, 2007, 37(1): 80-98. (in Chinese) 黄争鸣, 张华山. 纤维增强复合材料强度理论的研究现状与发展趋势——"破坏分析奥运会"评估综述. 力学进展, 2007, 37(1): 80-98.
[3] Huang Z M, Zhang R J. On the ultimate strength of a fiber reinforced composite laminate subjected to lateral loads. Acta Materiae Compositae Sinica, 2005, 22(2): 148-159. (in Chinese) 黄争鸣, 张若京. 复合材料结构受横向载荷作用的强度问题. 复合材料学报, 2005, 22(2): 148-159.
[4] Richard R M, Blacklock J R. Finite element analysis of inelastic structures. AIAA Journal, 1969, 7(3): 432-438.
[5] Hahn H T, Tsai S W. Nonlinear elastic behavior of unidirection composite laminate.Journal of Composite Materials, 1973, 7(1): 102-118.
[6] Jones R M, Nelson J R. A new materials model for the nonlinear biaxial behavior of ATJ—S graphite. Journal of Composite Materials, 1975, 9(1): 10-27.
[7] Xia Y M, Yang B C, Xu Z. Nonlinear constitutive relation of unidirectional composite laminae. Acta Materiae Compositae Sinica, 1986, 3(4): 44-49. (in Chinese) 夏源明, 杨报昌, 徐祯. 单向复合材料板的非线性本构关系. 复合材料学报, 1986, 3(4): 44-49.
[8] Jiang Y Q, Lu F S, Gu Z J. Mechanics of composites. Xi’an: Xi’an Jiaotong University Press, 1990: 58-88. (in Chinese) 蒋咏秋, 陆逢升, 顾志建. 复合材料力学. 西安: 西安交通大学出版社, 1990: 58-88.
[9] Whitney J M. Stress analysis of thick laminated composite and sandwich plates. Journal of Composite Materials, 1972, 6(3): 426-440.
[10] Chou P C, Carleone J, Hsu C M. Elastic constants of layered media. Journal of Composite Materials, 1972, 6(1): 80-93.
[11] Bogetti T A, Hoppel C P R, Harik V M, et al. Predicting the nonlinear response and progressive failure of composite laminates. Composite Science and Technology, 2004, 64(3-4): 329-342.
[12] Hashin Z.Failure criteria for unidirectional fiber composites. Journal of Applied Mechanics, 1980, 47(2): 329-334.
[13] Camanho P P, Matthews F L. A progressive damage model for mechanically fastened joints in composite laminates. Journal of Composite Materials, 1999, 33(24): 2248-2280.
[14] Sun C T, Liao W C. Analysis of thick section composite laminates using effective moduli. Composite Materials, 1990, 24(9): 977-993.
[15] Puck A, Schurmannb H. Failure analysis of FRP laminates by means of physically based phenomenological models. Composite Science and Technology, 2002, 62(12-13): 1633-1662.
[16] Soden P D, Hinton M J, Kaddour A S. Lamina properties, lay-up configuration and loading conditions for a range of fiber reinforced composite laminates. Composite Science and Technology, 1998, 58(7): 1011-1022.
[17] O’Higgins R M, Padhi G S, McCarthy M A, et al. Experimental and numerical study of the open-hole tensile strength of carbon/epoxy composite. Mechanics of Composite Materials, 2004, 40(4): 269-278.
[18] Tan S C. A progressive failure model for composite laminates containing openings. Journal of Composite Materials, 1991, 25(5): 556-557.
[19] Tan S C, Perez J. Progressive failure of laminated composites with a hole under compressive loading. Journal of Reinforced Plastics and Composites, 1993, 12(10): 1043-1057.
[20] Nuimer R J, Tan S C. Constitutive relations of a cracked composite lamina. Journal of Composite Materials, 1988, 22(4): 306-321.
[21] Tan S C, Nuimer R J. A theory for progressive matrix cracking in composite laminates. Journal of Composite Materials, 1989, 23(10): 1029-1047.
[22] Zhu J F, Wang H. Nonlinear finite element of aircraft structures. Shanghai: Shanghai Jiao Tong University Press, 2011: 61-67. (in Chinese) 朱菊芬, 汪海. 飞机结构非线性有限元. 上海: 上海交通大学出版社, 2011: 61-67.
[23] Liu C W. Study of strength evaluation of composite laminates and software development. Shanghai: School of Aeronautics and Astronautics, Shanghai Jiao Tong University, 2011. (in Chinese) 刘长玮. 复合材料层压板强度评估方法研究与软件开发. 上海: 上海交通大学航空航天学院, 2011.

Nonlinear Stiffness Analysis of Thick Composite Laminate Under Biaxial Load

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