含初始脱粘缺陷复合材料加筋壁板渐进压溃过程的数值模拟

玻璃钢/复合材料 ›› 2017, Vol. 0 ›› Issue (11): 12-18.

含初始脱粘缺陷复合材料加筋壁板渐进压溃过程的数值模拟

邹华民¹,崔向斌²,任明法^1,3*,常鑫¹

1.大连理工大学工程力学系,大连116024;
2.中国航天科技集团公司四院41所,西安710025;
3.大连理工大学工业装备结构分析国家重点实验室,大连116024

收稿日期:2017-05-05 出版日期:2017-11-28 发布日期:2017-11-28
通讯作者: 任明法(1974-),男,博士,副教授,主要从事复合材料及其结构力学等方面的研究,renmf@dlut.edu.cn。
作者简介:邹华民(1993-),男,硕士,主要从事复合材料结构承载性能分析方面的研究。
基金资助:
国家自然科学基金(11372058);973国家重点基础研究发展计划(2014CB046506,2014CB049000)

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

ZOU Hua-min¹, CUI Xiang-bin², REN Ming-fa^{1, 3*}, CHANG Xin¹

1.Department of Engineering Mechanics, Dalian University of Technology, Dalian 116024, China;
2.The 41st Institute of Fourth Academy of Aerospace Science and Technology Corporation,Xi′an 710025, China;
3.State Key Laboratory of Structural Analysis for Industrial Equipment,Dalian University of Technology, Dalian 116024, China

Received:2017-05-05 Online:2017-11-28 Published:2017-11-28

摘要/Abstract

摘要： 建立了预测含初始脱粘缺陷复合材料加筋壁板渐进压溃响应的数值分析模型。该模型综合考虑了复合材料层合板的纤维失效、基体失效和纤维-基体剪切失效三种典型的面内损伤模式,并通过编写用户自定义材料子程序VUMAT实现面内失效类型的判断和相应材料性能的折减;在壁板和筋条连接界面应用虚裂纹闭合技术(VCCT)计算层间裂纹前缘的应变能释放率,并结合B-K混合模式准则控制缺陷的起裂以模拟脱粘的扩展演化过程;采用显式动力学方法准静态分析结构在压缩载荷下的屈曲、后屈曲直至最终压溃的响应过程。数值分析结果与文献试验、数值结果吻合良好,验证了模型的合理性和有效性,并详细研究了复合材料脱粘加筋壁板的损伤演化过程和渐进压溃行为。

关键词: 脱粘缺陷, 复合材料, 加筋壁板, 后屈曲, 压溃, 损伤演化

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

中图分类号:

TB332

邹华民,崔向斌,任明法,常鑫. 含初始脱粘缺陷复合材料加筋壁板渐进压溃过程的数值模拟[J]. 玻璃钢/复合材料, 2017, 0(11): 12-18.

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.

参考文献

[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.