On the robustness of finite element procedures based on Virtual Crack Closure Technique and fail release approach for delamination growth phenomena. Definition and assessment of a novel methodology
Source abstract
Abstract
Numerical procedures based on the combined use of the Virtual Crack Closure Technique and of a fail release approach have been widely used to simulate delamination growth phenomena of composite material structures. This paper starts explaining why this kind of methodologies might not be robust due to mesh and load step size dependency and introduces a novel approach able to cope with the problems identified. Finally the effectiveness and robustness of the proposed procedure, implemented into a commercial finite element software by means of user subroutines, are assessed by comparing the obtained numerical results for a delamination growth phenomenon against literature experimental data on a stiffened panel with a circular embedded delamination under compressive load.
Source: openaire · Quality: candidate unverified · Source record ↗
Research context
OpenAlex topics: Mechanical Behavior of Composites · Composite Structure Analysis and Optimization · Structural Analysis of Composite Materials
SciVX discovery tags are terminology-based. OpenAlex topics are source-provided classifications.
References (32)
Show source-provided references
1. One dimensional modelling of failure in laminated plates by delamination buckling10.1016/0020-7683(81)90014-7 ↗
2. Large deformation effects in the post buckling behaviour of composites with thin delaminations10.2514/3.10153 ↗
3. A finite element calculation of stress intensity factors by a modified crack closure integral10.1016/0013-7944(77)90013-3 ↗
4. Calculation of strain-energy release rates with higher order an singular finite elements10.1016/0013-7944(87)90220-7 ↗
5. A virtual crack closure technique for calculating stress intensity factors for cracked three dimensional bodies10.1007/BF00035103 ↗
6. Krueger R. The virtual crack closure technique: history, approach and applications. NASA/CR-2002-211628.
7. Three-dimensional analysis of a postbuckled embedded delamination10.1177/002199838902300901 ↗
8. A numerical and experimental study of delaminated layered composites10.1177/002199839402800904 ↗
9. Analysis of a laminate with a postbuckled embedded delamination, including contact effects10.1177/002199839202601008 ↗
10. Influence of contact phenomena on embedded delaminations growth in composites10.2514/2.2029 ↗
11. Modeling damage propagation in composite plates with embedded delamination under compressive load10.1177/0021998308092199 ↗
12. Strain energy release rate calculation for a moving delamination front of arbitrary shape based on the virtual crack closure technique. Part I: formulation and validation10.1016/j.engfracmech.2005.07.013 ↗
13. Strain energy release rate calculation for a moving delamination front of arbitrary shape based on the virtual crack closure technique. Part II: sensitivity study on modeling details10.1016/j.engfracmech.2005.07.014 ↗
14. Mabson GE, Deobald LR, Dopker B, Hoyt DM, Baylor JS, Graesser DL. Fracture interface elements for static and fatigue analysis. In: 16th international conference on composite materials. Kyoto, Japan: ICCM-16; 2007.
15. Deobald L, Mabson GE, Dopker B. Interlaminar fatigue elements for crack growth based on virtual crack closure technique. In: 48th AIAA/ASME/ASCE/AHS/ASC structures, structural dynamics, and materials conference. Honolulu, Hawaii: AIAA-2007-2091; 2007.10.2514/6.2007-2091 ↗
16. Modeling delamination growth in laminated composites10.1016/S0266-3538(01)00023-9 ↗
17. Efficient modeling of postbuckling delamination growth in composite laminates using plate elements10.2514/3.13038 ↗
18. Pietropaoli E, Riccio A. A global/local finite element approach for predicting interlaminar and intralaminar damage evolution in composite stiffened panels under compressive load. Accepted for publication in applied composite materials; 2010.10.1007/s10443-010-9135-1 ↗
19. Compression and post-buckling damage growth and collapse analysis of flat composite stiffened panels10.1016/j.compscitech.2008.07.017 ↗
20. Strain energy release rate formulae for skin-stiffener debond modeled with plate elements10.1016/0013-7944(95)00088-7 ↗
21. Krueger R. O’Brien T.K.A shell/3D modeling technique for the analysis of delaminated composite laminates. NASA/TM-2000-210287.10.1016/S1359-835X(00)00133-0 ↗
22. Numerical simulation of mixed-mode progressive delamination in composite materials10.1177/0021998303034505 ↗
23. Turon A, Camanho PP, Costa J, Dávila CG. An interface damage model for the simulation of delamination under variable-mode ratio in composite materials. NASA/TM-2004-213277.
24. On transition of delamination growth behaviour for compression loaded composite panels10.1016/S0020-7683(01)00114-7 ↗
25. Krueger R. An approach to assess delamination propagation simulation capabilities in commercial finite element codes. NASA TM/2008-215123.
26. Krueger R, Goetze D. Influence of finite element software on energy release rates computed using the virtual crack closure technique. NASA/CR-2006-214523.
27. The effect of defects on the performance of post-buckled CFRP stringer-stiffened panels10.1016/S1359-835X(03)00098-8 ↗
28. Reeder JR. An evaluation of mixed-mode delamination failure criteria. NASA-TM-104210.
29. Ferrie CH, Rousseau CQ. A method of applying VCCT to corner crack nodes. In: Proceedings of the American society for composites – 16th annual technical conference on composite materials. Blacksburg (VA), USA; 2001.
30. Delamination growth and thresholds in a carbon/epoxy composite under fatigue loading10.1520/CTR10914J ↗
31. Tsamtsakis D, Wevers M, De Meester P. Damage monitoring during fatigue loading of quasi-isotropic carbon epoxy laminates. In: Van Hemelrijck, Annastassopulos. editors. Non destructive testing. Balken Rotterdam; 1996. ISBN 905410595X.10.4028/www.scientific.net/MSF.210-213.125 ↗
32. ANSYS 11. User manual.