NASA Logo

NTRS

NTRS - NASA Technical Reports Server

Back to Results
Benchmarking Mixed Mode Failure in Progressive Damage and Failure Analysis MethodsThe verification and validation of progressive-damage-analysis finite element methods are difficult but critical tasks to undertake during their development. Verification exercises assess whether a predictive analysis tool produces results that are consistent with the fundamental concepts and assumptions of the tool under evaluation. Ideally, closed-form analytical solutions can be derived for which method verification results can be compared. Problems selected for computational tool verification are often simple and isolate individual features of the tool. In the case of progressive damage finite element methods, verifications should be performed to evaluate the ability of the model to predict the initiation of damage and its growth through the finite element mesh under a variety of conditions. Mabson et al. proposed a test case of a unidirectional, fiber-reinforced plate with a center crack subjected to tensile loads to evaluate matrix crack propagation predictions. The problem was modeled using the Abaqus Hashin continuum damage mechanics (CDM) model for fiber-reinforced composites. Different combinations of matrix strengths and element sizes were used in the simulations, and the results were compared to a closed-form solution based on linear elastic fracture mechanics (LEFM). It was determined that the Abaqus CDM model could predict the LEFM solution of Mode I cracks only when the finite element mesh density met specific requirements based on the material properties. This paper presents closed-form LEFM solutions for a center notch mixed mode (CNMM) verification problem. Parametric finite element analyses were developed using progressive damage analysis methods of both the Discrete Damage Mechanics (DDM) and CDM classes. The progressive damage analysis methods applied in the analyses of the CNMM problem include CompDam and the Floating Node Method. Analyses were conducted with various mode mixities and element sizes to verify that the damage models were working as intended and to identify any limits of applicability.


Document ID
20190033160
Acquisition Source
Langley Research Center
Document Type
Conference Paper
Authors
Leone, Frank
(NASA Langley Research Center Hampton, VA, United States)
Ramnath, Madhavadas
(Boeing Company Hampton, VA, United States)
Hyder, Imran
(Boeing Company Hampton, VA, United States)
Wanthal, Steven
(Boeing Company Hampton, VA, United States)
Schaefer, Joseph D.
(Boeing Company Hampton, VA, United States)
Mabson, Gerald
(Boeing Company Hampton, VA, United States)
Date Acquired
November 22, 2019
Publication Date
September 24, 2019
Subject Category
Systems Analysis And Operations Research
Chemistry And Materials (General)
Report/Patent Number
NF1676L-29474
Report Number: NF1676L-29474
Meeting Information
Meeting: American Society of Composites Technical Conference
Location: Seattle, WA
Country: United States
Start Date: September 24, 2018
End Date: September 26, 2018
Sponsors: American Society for Composites
Funding Number(s)
WBS: 826611.04.07.01
CONTRACT_GRANT: NNL09AA00A
Distribution Limits
Public
Copyright
Public Use Permitted.
No Preview Available