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    Methodology for Impact Modeling of Triaxial Braided Composites Using Shell Elements

    Source: Journal of Aerospace Engineering:;2009:;Volume ( 022 ):;issue: 003
    Author:
    Xuetao Li
    ,
    Wieslaw K. Binienda
    ,
    Justin D. Littell
    DOI: 10.1061/(ASCE)0893-1321(2009)22:3(310)
    Publisher: American Society of Civil Engineers
    Abstract: In this paper, a two-dimensional triaxial braided composite model has been studied using the nonlinear explicit finite-element code LSDYNA. The unit cell consists of six subcells and material properties associated with shell element integration point simulate braiding architecture. The local material properties were selected by correlation of the global behavior of a coupon model with static specimen tests. By changing subcell size and orientation angle at integration points, different braids architectures were obtained. Panel ballistic models were performed with benefits of computation efficiency of shell elements. Mechanical properties, panel impact threshold velocities, and failure initiations for braids with bias angles of 75, 60, 45, and 30° were studied. Boundary effects were also investigated.
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      Methodology for Impact Modeling of Triaxial Braided Composites Using Shell Elements

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    http://yetl.yabesh.ir/yetl1/handle/yetl/45173
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    contributor authorXuetao Li
    contributor authorWieslaw K. Binienda
    contributor authorJustin D. Littell
    date accessioned2017-05-08T21:16:28Z
    date available2017-05-08T21:16:28Z
    date copyrightJuly 2009
    date issued2009
    identifier other%28asce%290893-1321%282009%2922%3A3%28310%29.pdf
    identifier urihttp://yetl.yabesh.ir/yetl/handle/yetl/45173
    description abstractIn this paper, a two-dimensional triaxial braided composite model has been studied using the nonlinear explicit finite-element code LSDYNA. The unit cell consists of six subcells and material properties associated with shell element integration point simulate braiding architecture. The local material properties were selected by correlation of the global behavior of a coupon model with static specimen tests. By changing subcell size and orientation angle at integration points, different braids architectures were obtained. Panel ballistic models were performed with benefits of computation efficiency of shell elements. Mechanical properties, panel impact threshold velocities, and failure initiations for braids with bias angles of 75, 60, 45, and 30° were studied. Boundary effects were also investigated.
    publisherAmerican Society of Civil Engineers
    titleMethodology for Impact Modeling of Triaxial Braided Composites Using Shell Elements
    typeJournal Paper
    journal volume22
    journal issue3
    journal titleJournal of Aerospace Engineering
    identifier doi10.1061/(ASCE)0893-1321(2009)22:3(310)
    treeJournal of Aerospace Engineering:;2009:;Volume ( 022 ):;issue: 003
    contenttypeFulltext
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