NASA LogoNTRSNTRS - NASA Technical Reports ServerSearchmore_vertCollectionsAboutNewsHelpLogin Back to ResultsIncorporation of Failure Into an Orthotropic Three-Dimensional Model with Tabulated Input Suitable for Use in Composite Impact ProblemsThe need for accurate material models to simulate the deformation, damage and failure of polymer matrix composites under impact conditions is becoming critical as these materials are gaining increased use in the aerospace and automotive communities. The aerospace community has identified several key capabilities which are currently lacking in the available material models in commercial transient dynamic finite element codes. To attempt to improve the predictive capability of composite impact simulations, a next generation material model is being developed for incorporation within the commercial transient dynamic finite element code LS-DYNA. The material model, which incorporates plasticity, damage and failure, utilizes experimentally based tabulated input to define the evolution of plasticity and damage and the initiation of failure as opposed to specifying discrete input parameters such as modulus and strength. The plasticity portion of the orthotropic, three-dimensional, macroscopic composite constitutive model is based on an extension of the Tsai-Wu composite failure model into a generalized yield function with a non-associative flow rule. For the damage model, a strain equivalent formulation is used to allow for the uncoupling of the deformation and damage analyses. In the damage model, a semi-coupled approach is employed where the overall damage in a particular coordinate direction is assumed to be a multiplicative combination of the damage in that direction resulting from the applied loads in various coordinate directions. For the failure model, a tabulated approach is utilized in which a stress or strain based invariant is defined as a function of the location of the current stress state in stress space to define the initiation of failure. Failure surfaces can be defined with any arbitrary shape, unlike traditional failure models where the mathematical functions used to define the failure surface impose a specific shape on the failure surface. In the current paper, the complete development of the failure model is described and the generation of a tabulated failure surface for a representative composite material is discussed.Document ID20170004667Acquisition SourceGlenn Research CenterDocument TypeTechnical Memorandum (TM)AuthorsGoldberg, Robert K.*(NASA Glenn Research Center Cleveland, OH United States)*Carney, Kelly S.*(George Mason Univ. Fairfax, VA, United States)*Dubois, Paul*(George Mason Univ. Fairfax, VA, United States)*Hoffarth, Canio*(Arizona State Univ. Tempe, AZ, United States)*Khaled, Bilal*(Arizona State Univ. Tempe, AZ, United States)*Shyamsunder, Loukham*(Arizona State Univ. Tempe, AZ, United States)*Rajan, Subramaniam*(Arizona State Univ. Tempe, AZ, United States)*Blankenhorn, Gunther*(Livermore Software Technology Corp. CA, United States)*Date AcquiredMay 23, 2017Publication DateMay 1, 2017Subject CategoryStructural MechanicsReport/Patent NumberGRC-E-DAA-TN40629NASA/TM-2017-219492E-19360Funding Number(s)CONTRACT_GRANT: NNC15CA32CWBS: WBS 826611.04.03.01Distribution LimitsPublicCopyrightPublic Use Permitted.KeywordsImpactFinite Element MethodPolymer Matrix CompositesAvailable DownloadsNameType20170004667.pdfSTIcloud_downloadcontent_copyvisibilityRelated RecordsThere are no records associated with this record.visibility_offNo Preview Available
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