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Combining Progressive Nodal Release with the Virtual Crack Closure Technique to Model Fatigue Delamination Growth Without Re-MeshingThe present work summarizes an approach to model mixed-mode 3D fatigue crack growth using the Virtual Crack Closure Technique (VCCT) without requiring re-meshing. It is demonstrated that the proposed approach can be used to simulate crack shapes that do not conform to the underlying mesh. The proposed approach relies solely on Paris Law characterization data to model delamination growth. Growth is determined as a post-processing step at the end of each increment, and hence no convergence issues associated with the progressive nodal release are encountered. This approach can be readily applied using standard solid element formulations and is implemented via an interface user element in Abaqus/Standard.
Document ID
20180006194
Acquisition Source
Langley Research Center
Document Type
Conference Paper
Authors
Carvalho, N. V. De
(National Inst. of Aerospace Hampton, VA, United States)
Krueger, R.
(National Inst. of Aerospace Hampton, VA, United States)
Mabson, G. E.
(Boeing Co. Seattle, WA, United States)
Deobald, L. R.
(Boeing Co. Seattle, WA, United States)
Date Acquired
October 9, 2018
Publication Date
January 8, 2018
Subject Category
Computer Programming And Software
Report/Patent Number
NF1676L-27504
Report Number: NF1676L-27504
Meeting Information
Meeting: AIAA SciTech
Location: Kissimmee, FL
Country: United States
Start Date: January 8, 2018
End Date: January 12, 2018
Sponsors: American Inst. of Aeronautics and Astronautics
Funding Number(s)
CONTRACT_GRANT: NNL09AA00A
WBS: WBS 826611.04.07.01
Distribution Limits
Public
Copyright
Public Use Permitted.
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