面内弯曲载荷作用下两边简支两边固支复合材料层合板的屈曲

doi:10.7527/S1000-6893.2013.0464

Abstract

Abstract:

In order to provide a stability analysis method of composite airframe structures, this paper presents a numerical solution method for the buckling of SSCC composite laminates (laminates having two parallel edges simply supported and the remaining parallel edges clamped) based on the Levy form series and finite-difference method. First, the deflection function is transformed to a discrete form by the finite-difference method; then, the system of equations is supplemented by the boundary conditions; finally, the critical buckling load is obtained through solving a generalized eigenvalue problem. Numerical examples are utilized to verify the present method on both isotropic and composite plates. The comparison of the present method and a finite element method (FEM) is conducted as well. The result shows that the present method has high accuracy and provides a new way for the buckling analysis of composite plates.

Key words: composite laminate, in-plane pure bending load, finite-difference method, buckling, critical buckling load

CLC Number:

V214.8
TB332

YUAN Jianfeng, NI Zao, CHEN Baoxing. Buckling of SSCC Composite Laminates Under In-plane Bending Load[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2014, 35(4): 1026-1033.

References

[1] Leissa A W. Buckling of laminated composite plates and shells panels, AFWAL-TR-85-3069. Columbus, OH: The Ohio State University, 1985.

[2] Sun J J, Zhang X J, Gong Z F, et al. Failure mechanism study on omega stringer debonding[J]. Acta Aeronautica et Astronautica Sinica, 2013, 34(7): 1616-1626. (in Chinese) 孙晶晶, 张晓晶, 宫占峰, 等. 复合材料帽型筋条脱粘的失效机理分析[J]. 航空学报, 2013, 34(7): 1616-1626.

[3] He E M, Hu Y Q, Zhang Z, et al. 3-D laminated model and dynamic response analysis of FGM panels in thermal-acoustic environments[J]. Acta Aeronautica et Astronautica Sinica, 2013, 34(6): 1293-1300. (in Chinese) 贺尔铭, 胡亚琪, 张钊, 等. FGM板三维层合模型及热-噪声载荷下的动态响应研究[J]. 航空学报, 2013, 34(6): 1293-1300.

[4] Wu C L, Duan S H, Li X X. Buckling investigation of composite corrugated panel subject to shear loads[J]. Acta Aeronautica et Astronautica Sinica, 2011, 32(8): 1453-1460. (in Chinese) 吴存利, 段世慧, 李新祥. 复合材料波纹板剪切载荷作用下的屈曲试验与分析[J]. 航空学报, 2011, 32(8): 1453-1460.

[5] Lu W S, Ma Y C, Liang W, et al. Analysis system of stability and strength for airframe composite stiffened plate/shell[J]. Acta Aeronautica et Astronautica Sinica, 2009, 30(5): 895-900. (in Chinese) 卢文书, 马元春, 梁伟, 等. 机身复合材料加筋板壳的稳定性及强度分析系统[J]. 航空学报, 2009, 30(5): 895-900.

[6] Timoshenko S, Gere J. Theory of elastic stability[M]. 2nd ed. New York: McGraw-Hill Book Company, Inc., 1963: 373-379.

[7] Leissa A W, Kang J H. Exact solutions for vibration and buckling of an SS-C-SS-C rectangular plate loaded by linearly varying in-plane stresses[J]. International Journal of Mechanical Sciences, 2002, 44(9): 1925-1945.

[8] Leissa A W, Kang J H. Exact solutions for the buckling of rectangular plates having linearly varying in-plane loading on two opposite simply supported edges[J]. International Journal of Solids and Structures, 2005, 42(14): 4220-4238.

[9] Panda S K, Ramachandra L S. Buckling of rectangular plates with various boundary conditions loaded by non-uniform inplane loads[J]. International Journal of Mechanical Sciences, 2010, 52(6): 819-828.

[10] Lekhnitskii S G. Anisotropic plates[M]. 2nd ed. NewYork: Gordon and Breach Science Publishers, Inc., 1968: 459-465.

[11] Papazoglou V J, Tsouvalis N G, Kyriakopoulos G D. Buckling of unsymmetrical laminates under linearly varying, biaxial in-plane loads, combined with shear[J]. Composite Structure, 1992, 20(3): 155-163.

[12] Zhong H Z, Gu C. Buckling of symmetrical cross-ply composite rectangular plates under a linearly varying in-plane load[J]. Composite Structure, 2007, 80(1): 42-48.

[13] Shufrin I, Rabinovitch O, Eisenberger M. Buckling of symmetrically laminated rectangular plates with general boundary conditions—a semi analytical approach[J]. Composite Structure, 2008, 82(4): 521-531.

[14] Lopatin A V, Morozov E V. Buckling of the SSFF rectangular orthotropic plate under in-plane pure bending[J]. Composite Structure, 2009, 90(3): 287-294.

[15] Lopatin A V, Morozov E V. Buckling of the CCFF orthotropic rectangular plates under in-plane pure bending[J]. Composite Structure, 2010, 92(6): 1423-1431.

[16] Lopatin A V, Morozov E V. Buckling of the SSCF rectangular orthotropic plate subjected to linearly varying in-plane loading[J]. Composite Structure, 2011, 93(7): 1900-1909.

[17] Kassapoglou C. Design and analysis of composite structures: with applications to aerospace structures[M]. Chicester: John Wiley & Sons, 2010: 86-91.

[18] Institute of Aeronautics China. Handbook of aircraft design: Volume 9[M]. Beijing: Aviation Industry Press, 2001: 398-399. (in Chinese) 中国航空研究院. 飞机设计手册: 第九册[M]. 北京: 航空工业出版社, 2001: 398-399.

Buckling of SSCC Composite Laminates Under In-plane Bending Load

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