Numerical Analysis of Delamintation Growth for Stiffened Composite Laminated Plates

BAI Rui-xiang; CHEN Hao-ran

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BAI Rui-xiang, CHEN Hao-ran. Numerical Analysis of Delamintation Growth for Stiffened Composite Laminated Plates[J]. Applied Mathematics and Mechanics, 2004, 25(4): 368-378.

Citation:

BAI Rui-xiang, CHEN Hao-ran. Numerical Analysis of Delamintation Growth for Stiffened Composite Laminated Plates[J]. Applied Mathematics and Mechanics, 2004, 25(4): 368-378.

Citation:

BAI Rui-xiang, CHEN Hao-ran. Numerical Analysis of Delamintation Growth for Stiffened Composite Laminated Plates[J]. Applied Mathematics and Mechanics, 2004, 25(4): 368-378.

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Numerical Analysis of Delamintation Growth for Stiffened Composite Laminated Plates

Dalian University of Technology, Dalian 116024, P. R. China

Received Date: 2002-07-23
Rev Recd Date: 2003-01-30
Publish Date: 2004-04-15

Abstract

Abstract

A study of postbudding and delamination propagation behavior in delaminated stiffened composite plies is presented. A methodology is proposed for simulating the multi-failure responses,such as initial and postbuckling,delamination onset and propagation,etc. A finite element analysis was conducted on the bass of the Mindlin first order shear effect theory and the von-Kûrmûn nonlinear deformation assumption The total energy release rate used as the criteria of delamination growth was estimatedwith virtual aback closure technique (VCGT). A self-adaptive grid moving technology was adopted to model the delalrunation growth prooess. Moreover,the contact effect along delaminafion front was also considered during the numerical simulation process.By some nurrerical examples,the influence of distribution a1d location of stiffener,configuration and size of the delamination,boundary condition and contact effect upon the delamination growth behavior of the stiffened composite plates were investigated The method and numerical condusion provided should be of great value to engineers dealing with composite structures.
- finite element method,
- postbuckling,
- energy release rate,
- delamination growth,
- stiffened composite laminated plate

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References(21)

References

[1]	Whitecomb J D. Finite element analysis of instability related delamination growth[J].Composite Mater,1981,15(9): 403—426. doi: 10.1177/002199838101500502
[2]	Whitecomb J D. Parametric analytical study of instability-related delamination growth[J].Composites Science and Technology,1986,25(1):18—48.
[3]	Chai H, Babcok C D, Knauss W G. One delamination modeling of failure in laminated plates by delamination buckling[J].Solids Strut,1981,17(1):1069—1083. doi: 10.1016/0020-7683(81)90014-7
[4]	Ramkumar R L. Fatigue degradation in compressively loaded composite laminates[R]. NASA CR-165681, 1981.
[5]	Ramkumar R L. Performance of a quantitative study for instability related laminates[R]. NASA CR-166046, 1983.
[6]	Whitecomb J D, Shivakumar K N. Strain-energy release rate analysis of a laminate with a postbuckled delamination. Numerical methods in fracture mechanics[R]. NASA TM-89091, 1987.
[7]	Shivakumar K N, Whitecomb J D. Buckling of a sublaminate in a quasi-isotropic composite[J].Composite Mater,1985,19(1):2—18. doi: 10.1177/002199838501900101
[8]	Chai H. Buckling and post-buckling behavior of elliptical plates: part analysis[J].Journal Applied Mechanics,1990,57(4):981—988. doi: 10.1115/1.2897671
[9]	Riccio A, Scaramuzzino F, Perugini P. Embedded delamination growth in composite panels under compressive load[J].Composites, Part B,2001,32(3): 209—218. doi: 10.1016/S1359-8368(00)00057-3
[10]	Shen F, Lee K H, Tay T E. Modeling delamination growth in laminated composites[J].Composites Science and Technology, 2001, 61(9):1239—1251. doi: 10.1016/S0266-3538(01)00023-9
[11]	孙先念, 陈浩然, 苏长健,等. 含分层损伤复合材料层合板分层扩展研究[J]. 力学学报, 2000,32(2):223—232.
[12]	陈浩然, 尹向勇, 郭兆璞,等. 含分层损伤复合材料加筋板非线性热屈曲分析[J]. 宁夏大学学报(自然科学版), 1999,20(3): 228—237.
[13]	陈浩然, 尹向勇, 郭兆璞,等. 含有分层损伤复合材料加筋层合板的屈曲性态研究[J]. 计算力学学报, 2000,17(2):156—161.
[14]	Kong C W, Hong C S, Kim C G. Post buckling strength of stiffened composite plates with impact damage[J]. AIAA J, 2000,38(10)：1956—1964. doi: 10.2514/2.851
[15]	Ishikawa T, Matsushima M,Hayashi Y. Improved correlation of predicted and experimental initial buckling stress of composite stiffened panels[J].Composite Structures,1993,26(1):25—38. doi: 10.1016/0263-8223(93)90041-N
[16]	孙先念, 陈浩然, 陈绍杰. 含分层损伤复合材料层合板前后屈曲行为研究[J].航空学报, 1999,20(3):224—229.
[17]	白瑞祥, 陈浩然. 含界面开裂损伤的复合材料夹层板线性和非线性热-机械力屈曲性态研究[J]. 工程力学,2000,1(增刊):383—386.
[18]	陈浩然, 白瑞祥. 含损伤复合材料夹层板剩余压缩强度的数值分析[J]. 大连理工大学学报,2001,41(4):404—411.
[19]	CHEN Hao-ran, BAI Rui-xiang. Postbuckling behavior of composite sandwich plate containing interfacial debonding[A].In:ZHANG Yao Ed.Proceeding of the 13th International Composite Conference ICCM13[C].Beijing:Scientific and Technical Documents Publishing House,2001, 1—6.
[20]	Rizzo A R. FEA gap elements choosing the right stiffness[J]. Mechanical Engineering,1991,113(6): 57—59.
[21]	Rybicki E F, Kanninen M F. A finite element calculation of stress intensity factors by modified crack closure integral[J].Engineering Fracture Mechanics,1977,9(3)：931—938. doi: 10.1016/0013-7944(77)90013-3