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圆柱壳板非线性屈曲的分叉解 被引量:3

Nonlinear Bifurcation Buckling Solution of Circular Cylindrical Shell Panel
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摘要 采用商用有限元分析软件MSC/Nastran,对两直边铰支、其余两边自由的各向同性圆柱壳板中心受横向集中载荷下的非线性屈曲和后屈曲过程进行了分析,简单地采用了不对称网格技术就可获得该基准问题的分叉屈曲解,计算得到分叉屈曲解的极限载荷比基准解极限载荷小10%左右。对采用了多种不对称网格划分得到的模型进行了分析,以研究不同网格划分对最终结果的影响。结果表明,虽然不对称网格技术十分简单,但是也有一定的局限性,文中给出了能得到分叉屈曲解的网格划分方法,还分析了类似的复合材料圆柱壳板问题。研究结果表明,即使采用对称网格划分也能够得到该问题的分叉屈曲解,并阐述了其原因。 Nonlinear buckling and post-buckling of the circular cylindrical panel with its straight edges hinged and the other free edges subjected to a transversely concentrated load at its center are analyzed by using the commercial finite element(FE) software MSC/Nastran. Its bifurcation buckling load is solution obtained hy using an asymmetric mesh technique (AMT). Computing data indicate that the limited load of bifurcation buckling solution is lower about 10% than that of the available benchmark solution. To study the effects of different meshes on the final results, various models obtained by different asymmetric meshes are used. It is shown that although the AMT is simple but it has some limitations. A meshing method for obtaining bifurcation buckling solution is given. A similar problem to a circular cylindrical composite panel is analyzed. The result shows show that the bifurcation buckling solution can also be obtained even with a symmetric mesh. Finally, the reasons are described.
出处 《南京航空航天大学学报》 EI CAS CSCD 北大核心 2008年第5期637-640,共4页 Journal of Nanjing University of Aeronautics & Astronautics
基金 国家自然科学基金(50675100)资助项目
关键词 有限元法 圆柱壳板 不对称网格技术 非线性屈曲 极限载荷 finite element method circular cylindrical shell panel asymmetric mesh technique nonlinear buckling limit load
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参考文献5

  • 1Mark W H, Michael P N, James H S. Shell buckling design criteria based on manufacturing imperfection signatures [J]. AIAA Journal, 2006, 44 (3) : 654-663.
  • 2Sabir A B, Lock A C. The application of finite elements to the large deflection geometrically non-linear behaviour of cylindrical shells [C]//Brebbia C A, Tottenham H,eds. Variational Methods in Engineering. Surrey: Southampton University Press, 1973: 66-75.
  • 3Wardle B L. The incorrect benchmark shell buckling solution [R]. AIAA 2006-2028, 2006.
  • 4Brogan F A, Rankin C C, Cabiness H D, et al. STAGS user manual-version 2.3 [M ]. Maryland, USA:Lockheed Martin Missiles and Space Co, Inc, 1996.
  • 5MSC Software. MSC/Nastran 2005 reference manual [M]. California, USA: MSC. Software Corporation, 2005.

同被引文献33

  • 1刘述伦,薛江红,王璠,刘人怀.含脱层纤维增强复合材料层合板在湿热环境下的屈曲分析[J].工程力学,2015,32(3):1-8. 被引量:8
  • 2Engelstad S P, Reddy J N, Knight N F. Postbuckling response and failure prediction of graphite/epoxy plates loaded in compression [J]. AIAA, 1992, 30(8): 2106-2113.
  • 3Kweon J H, Hong C S, Lee I C. Postbuckling compressive strength of graphite/epoxy laminated cylindrical panels loaded in compression[J]. AIAA, 1995, 33(2): 217-222.
  • 4Knight N F, Starnes J H. Postbuckling behavior of selected curved stiffened graphite epoxy panels loaded in axial compression [J]. AIAA, 1988, 26(3): 344-352.
  • 5Lee I C, Kim C G, Hong C S. Buckling and postbuckling behavior of stiffened composite panels loaded in compression [J]. AIAA, 1997, 35(1): 202-204.
  • 6Wardle B L, Lagace P A. Behavior of composite shells under transverse impact and quasi static loading [J].AIAA, 1998, 36(6), 1065-1073.
  • 7Wardle B L, Lagace P A, Tudela M A. Buckling response of transversely loaded composite shells Ⅰ: Experiments [J]. AIAA, 2004, 42(7): 1457-1464.
  • 8Wardle B L, Lagace P A, Tudela M A. Buckling response of transversely loaded composite shells Ⅱ : Numerical analysis [J]. AIAA, 2004, 42(7): 1465-1473.
  • 9Spottswood S M, Palazotto A N. Progressive failure analysis of a composite shell [J]. Composite Structures, 2001, 53(1) : 117-131.
  • 10Reddy Y S N, Reddy J N. Linear and non linear failure analysis of composite laminates with transverse shear [J]. Composite Science and Technology, 1992, 44(3): 227-255.

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