Failure Modeling in an Orthotropic Plastic Material Model Under Static and Impact Loading
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Failure Modeling in an Orthotropic Plastic Material Model Under Static and Impact Loading

Filetype[PDF-4.06 MB]


English
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  • Creators:
    Shyamsunder, Loukham
  • Corporate Creators:
    Arizona State University
  • Corporate Contributors:
    United States. Department of Transportation. Federal Aviation Administration. William J. Hughes Technical Center
  • Subject/TRT Terms:
  • Publication/ Report Number:
    DOT/FAA/TCTT-22/38
  • DOI:
  • Resource Type:
    Thesis
  • Geographical Coverage:
    United States
  • Corporate Publisher:
    United States. Department of Transportation. Federal Aviation Administration. William J. Hughes Technical Center
  • Abstract:
    An orthotropic elasto-plastic damage material model (OEPDMM) suitable for impact analysis of composite materials has been developed through a joint research project funded by the Federal Aviation Administration (FAA) and the National Aeronautics and Space Administration (NASA). The developed material model has been implemented into LS-DYNA®, a commercial finite element program. The material model is modular comprising of deformation, damage and failure sub-models. The deformation sub-model captures the rate and/or temperature dependent elastic and inelastic behavior via a visco-elastic-plastic formulation. The damage sub-model predicts the reduction in the elastic stiffness of the material. The failure sub-model predicts when there is no more load carrying capacity in the finite element and erosion of the element from the finite element model. Most of the input parameters required to drive OEPDMM are in the form of tabulated data. The deformation sub-model is driven by a set of tabulated stress-strain data for a given strain-rate and temperature combination. The damage sub-model is driven by tabulated damage parameter-strain data. Two failure sub-models have been implemented – Puck Failure Model and Generalized Tabulated Failure Model. Puck Failure Model requires scalar parameters as input whereas, the Generalized Tabulated Failure Model is driven by a set of equivalent failure strain tabulated data. The work presented here focuses on the enhancements made to OEPDMM with emphasis on the background, development, and implementation of the failure sub-models. OEPDMM is verified and validated using a carbon/epoxy fiber reinforced composite. Two validation tests are used to evaluate the failure sub-model implementation - a stacked-ply test carried out at room temperature under quasi-static tensile and compressive loadings, and several high-speed impact tests where there is significant damage and material failure of the impacted panel. Results indicate that developed procedures provide the analyst with a reasonable and systematic approach to building predictive impact simulation models.
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