NASA LogoNTRSNTRS - NASA Technical Reports ServerSearchmore_vertCollectionsAboutNewsHelpLogin Back to ResultsMultiscale Static Analysis of Notched and Unnotched Laminates Using the Generalized Method of CellsThe generalized method of cells (GMC) is demonstrated to be a viable micromechanics tool for predicting the deformation and failure response of laminated composites, with and without notches, subjected to tensile and compressive static loading. Given the axial [0], transverse [90], and shear [+45/-45] response of a carbon/epoxy (IM7/977-3) system, the unnotched and notched behavior of three multidirectional layups (Layup 1: [0,45,90,-45](sub 2S), Layup 2: [0,60,0](sub 3S), and Layup 3: [30,60,90,-30, -60](sub 2S)) are predicted under both tensile and compressive static loading. Matrix nonlinearity is modeled in two ways. The first assumes all nonlinearity is due to anisotropic progressive damage of the matrix only, which is modeled, using the multiaxial mixed-mode continuum damage model (MMCDM) within GMC. The second utilizes matrix plasticity coupled with brittle final failure based on the maximum principle strain criteria to account for matrix nonlinearity and failure within the Finite Element Analysis--Micromechanics Analysis Code (FEAMAC) software multiscale framework. Both MMCDM and plasticity models incorporate brittle strain- and stress-based failure criteria for the fiber. Upon satisfaction of these criteria, the fiber properties are immediately reduced to a nominal value. The constitutive response for each constituent (fiber and matrix) is characterized using a combination of vendor data and the axial, transverse, and shear responses of unnotched laminates. Then, the capability of the multiscale methodology is assessed by performing blind predictions of the mentioned notched and unnotched composite laminates response under tensile and compressive loading. Tabulated data along with the detailed results (i.e., stress-strain curves as well as damage evolution states at various ratios of strain to failure) for all laminates are presented.Document ID20160010559Acquisition SourceGlenn Research CenterDocument TypeTechnical Memorandum (TM)AuthorsNaghipour Ghezeljeh, Paria*(Ohio Aerospace Inst. Brook Park, OH, United States)*Arnold, Steven M.*(NASA Glenn Research Center Cleveland, OH United States)*Pineda, Evan J.*(NASA Glenn Research Center Cleveland, OH United States)*Stier, Bertram*(Technische Univ. Aachen, Germany)*Hansen, Lucas*(Michigan Univ. Ann Arbor, MI, United States)*Bednarcyk, Brett A.*(NASA Glenn Research Center Cleveland, OH United States)*Waas, Anthony M.*(Washington Univ. Seattle, WA, United States)*Date AcquiredAugust 24, 2016Publication DateAugust 1, 2016Subject CategoryComputer Programming And SoftwareStructural MechanicsComposite MaterialsReport/Patent NumberNASA/TM-2016-219084E-19211GRC-E-DAA-TN28252Funding Number(s)WBS: WBS 826611.04.03.01CONTRACT_GRANT: NNC13BA10BDistribution LimitsPublicCopyrightPublic Use Permitted.KeywordsGMCcomposite damage modelingmultiscale modelingAvailable DownloadsNameType20160010559.pdfSTIcloud_downloadcontent_copyvisibilityRelated RecordsThere are no records associated with this record.visibility_offNo Preview Available
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