NUMERICAL SIMULATION ON PROGRESSIVE COLLAPSE PROCESS OF COMPOSITESTIFFENED PANEL WITH INITIAL DEBONDING DEFECT

Abstract

Abstract: A numerical analysis model was established to study the progressive collapse behavior of composite stiffened panel with initial debonding defect. Three typical intralaminar damage modes including fiber failure, matrix failure and fiber-matrix shear failure were considered in the model. The user-defined material subroutine VUMAT was used to distinguish the in-plane failure types and to degrade the corresponding material properties. The Virtual Crack Closure Technique was applied to calculate the strain energy release rate of the interlaminar crack front and the onset of debond propagation was determined using the B-K mixed-mode criterion. The buckling and post-buckling processes up to collapse of the panel under compressive load were quasi-static solved by the explicit dynamic method. The reasonability and validity of the model were verified by the good agreement between the numerical analysis result and the literature′s experimental and numerical results, and the damage evolution processes and the progressive collapse behavior of the debonded panel were investigated in detail.

Key words: debonding defect, composite, stiffened panel, post-buckling, collapse, damage evolution

CLC Number:

TB332

ZOU Hua-min, CUI Xiang-bin, REN Ming-fa, CHANG Xin. NUMERICAL SIMULATION ON PROGRESSIVE COLLAPSE PROCESS OF COMPOSITESTIFFENED PANEL WITH INITIAL DEBONDING DEFECT[J]. Fiber Reinforced Plastics/Composites, 2017, 0(11): 12-18.

References

[1] Degenhardt R, Rolfes R, Zimmermann R, et al. COCOMAT-improved material exploitation of composite airframe structures by accurate simulation of postbuckling and collapse[J] . Composite Structures, 2006, 73(2): 175-178.
[2] 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.
[3] 刘璐, 关志东, 徐荣章, 等. 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[J] . 复合材料学报, 2014, 31(3): 749-758.
[4] 冀赵杰, 关志东, 黎增山, 等. 脱粘尺寸对复合材料单加筋板压缩性能的影响[J] . 北京航空航天大学学报, 2016, 42(10): 2169-2179.
[5] Suemasu H, Kurihara K, Arai K, et al. Compressive property degradation of composite stiffened panel due to debonding and delaminations[J] . Advanced Composite Materials, 2006, 15(2): 139-151.
[6] Yap J W H, Scott M L, Thomson R S, et al. The analysis of skin-to-stiffener debonding in composite aerospace structures[J] . Composite Structures, 2002, 57(1): 425-435.
[7] Yap J W H, Thomson R S, Scott M L, et al. Influence of post-buckling behaviour of composite stiffened panels on the damage criticality[J] . Composite Structures, 2004, 66(1): 197-206.
[8] Orifici A C. Degradation models for the collapse analysis of composite aerospace structures[D] . RMIT University, 2007.
[9] 张阿盈, 邓凡尘, 于飞, 等. 长桁与蒙皮脱粘对复合材料加筋板承载能力影响分析[J] . 强度与环境, 2014, 41(3): 44-50.
[10] Hashin Z. Failure criteria for unidirectional fiber composites[J] . Journal of Applied Mechanics, 1980, 47(2): 329-334.
[11] Chang F K, Lessard L B. Damage tolerance of laminated composites containing an open hole and subjected to compressive loadings: Part I-Analysis[J] . Journal of Composite Materials, 1991, 25(1): 2-43.
[12] Goyal V K, Jaunky N R, Johnson E R, et al. Intralaminar and interlaminar progressive failure analyses of composite panels with circular cutouts[J] . Composite Structures, 2004, 64(1): 91-105.
[13] Krueger R. Virtual crack closure technique: history, approach, and applications[J] . Applied Mechanics Reviews, 2004, 57(2): 109-143.
[14] Delamination behaviour of composites[M] . Elsevier, 2008.
[15] Camanho P P, Davila C G, De Moura M F. Numerical simulation of mixed-mode progressive delamination in composite materials[J] . Journal of Composite Materials, 2003, 37(16): 1415-1438.
[16] 朱跃峰. 基于ABAQUS的显式动力学分析方法研究[J] . 机械设计与制造, 2015(3): 107-109.
[17] Orifici A C, Inigo Ortiz de Zarate Alberdi, Thomson R S, et al. Compression and post-buckling damage growth and collapse analysis of flat composite stiffened panels[J] . Composites Science and Technology, 2008, 68(15): 3150-3160.