全部 标题 作者
关键词 摘要

OALib Journal期刊
ISSN: 2333-9721
费用:99美元

查看量下载量

相关文章

更多...

脱胶缺陷尺寸对复合材料加筋板屈曲及后屈曲特性的影响

, PP. 749-758

Keywords: 复合材料加筋板,脱胶缺陷,屈曲,后屈曲,影像云纹法,几何扰动

Full-Text   Cite this paper   Add to My Lib

Abstract:

为确定脱胶缺陷对复合材料加筋板屈曲及后屈曲特性的影响,对含不同脱胶缺陷工型筋条的复合材料加筋板进行了压缩试验研究。结果表明,30mm和50mm的缺陷对试验件承载能力影响很小,当缺陷尺寸增至80mm时,试验件后屈曲承载能力明显下降。借助超声检测技术对缺陷的扩展行为进行了监测,结果表明,当压缩载荷达到破坏载荷的85.3%时,预制缺陷的对角位置处出现扩展迹象。通过影像云纹法获得两半波和三半波失稳模态的形成过程。对失稳模态的监测结果还表明,随缺陷长度增加,该型加筋板的失稳模态从三半波向两半波转换。在试验基础上,利用ABAQUS软件建立有限元(FE)模型,依次进行了屈曲及后屈曲过程的数值模拟。屈曲分析用于获得试验件的失稳载荷及模态,在后屈曲分析中将失稳波形以几何扰动的形式引入FE模型,最终计算结果与试验结果基本吻合,表明该模型可以用于复合材料加筋板屈曲及后屈曲性能的预测。

References

[1]  Bisagni C, Cordisco P. An experimental investigation into the buckling and post-buckling of CFRP shells under combined axial and torsion loading [J]. Composite Structures, 2003, 60(4): 391-402.
[2]  Falzon B G, Steven G P. Buckling mode transition in hat-stiffened composite panels loaded in uniaxial compression [J]. Composites Structures, 1997, 37(2): 253-267.
[3]  Abramovich H, Weller T, Bisagni C. Buckling behavior of composite laminated stiffened panels under combined shear-axial compression [J]. Journal of Aircraft, 2008, 45(2): 402-413.
[4]  Falzon B G, Stevens K A, Davies G O. Postbuckling behaviour of a blade-stiffened composite panel loaded in uniaxial compression [J]. Composites Part A: Applied Science and Manufacturing, 2000, 31(5): 459-468.
[5]  Orifici A C, Shah S A, Herszberg I, et al. Failure analysis in postbuckled composite T-sections [J]. Composite Structures, 2008, 86(1-3): 146-153.
[6]  Stevens K A, Ricci R, Davies G A O. Buckling and postbuckling of composite structures [J]. Composites, 1995, 26(3): 189-199.
[7]  Oh S H, Kim K S, Kim C G. An efficient postbuckling analysis technique for composite stiffened curved panels [J]. Composite Structures, 2006, 74(3): 361-369.
[8]  Lynch C, Murphy A, Price M, et al. The computational post buckling analysis of fuselage stiffened panels loaded in compression [J]. Thin-Walled Structures, 2004, 42(10): 1445-1464.
[9]  Lanzi L. A numerical and experimental investigation on composite stiffened panels into post-buckling [J]. Thin-Walled Structures, 2004, 42(12): 1645-1664.
[10]  Liu P F, Hou S J, Chu J K, et al. Finite element analysis of postbuckling and delamination of composite laminates using virtual crack closure technique [J]. Composite Structures, 2011, 93(6): 1549-1560.
[11]  刘从玉, 许希武, 陈 康. 考虑脱粘的复合材料加筋板屈曲后屈曲及承载能力数值分析 [J]. 复合材料学报, 2010, 27(6): 158-166. Liu Congyu, Xu Xiwu, Chen Kang. Buckling, post-buckling and collapse analysis of stiffened composite panels with debonding damage [J]. Acta Materiae Compositae Sinica, 2010, 27(6): 158-166.
[12]  Jaberzadeh E, Azhari M. Elastic and inelastic local buckling of stiffened plates subjected to non-uniform compression using the galerkin method [J]. Applied Mathematical Modelling, 2009, 33(4): 1874-1885.
[13]  Ovesy H R, Assaee H. Buckling characteristics of some composite stiffened boxes under longitudinal compression or bending using finite strip approach [C] //44th AIAA/ASME/ASCE/AHS Structures, Structural Dynamics, and Materials Conference. Norfolk: AIAA, 2003: 1791.
[14]  Greenhalgh E, Meeks C, Clarke A, et al. The effect of defects on the performance of post-buckled CFRP stringer-stiffened panels [J]. Composites Part A: Applied Science and Manufacturing, 2003, 34(7): 623-633.
[15]  戴福隆, 沈观林, 谢惠民. 实验力学 [M]. 北京: 清华大学出版社, 2010: 390-411. Dai Fulong, Shen Guanlin, Xie Huimin. Mechanics of experiment [M]. Beijing: Tsinghua University Press. 2010: 390-411.
[16]  Benzeggagh M L, Kenane M. Measurement of mixed-mode delamination fracture toughness of unidirectional glass/epoxy composites with mixed-mode bending apparatus [J]. Composites Science and Technology, 1996, 56(4): 439-449.
[17]  Hilburger M W, Starnes Jr J H. Effects of imperfections of the buckling response of composite shells [J]. Thin-Walled Structures, 2004, 42(3): 369-397.
[18]  Degenhardt R, Kling A, Rohwer K, et al. Design and analysis of stiffened composite panels including post-buckling and collapse [J]. Computers & Structures, 2008, 86 (9): 919-929.

Full-Text

Contact Us

service@oalib.com

QQ:3279437679

WhatsApp +8615387084133