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    Improving Delamination Modeling via Inverse Analysis

    Source: Journal of Aerospace Engineering:;2024:;Volume ( 037 ):;issue: 005::page 04024056-1
    Author:
    Ashutosh Maurya
    ,
    Mohammed Raihan
    ,
    Subramaniam Rajan
    DOI: 10.1061/JAEEEZ.ASENG-5613
    Publisher: American Society of Civil Engineers
    Abstract: Developing constitutive models that can be used to model composite structural systems subjected to impact loads where modeling damage, failure, and delamination are critical is a challenging task. Often processing experimental data to develop the composite material model and, especially, the delamination model can be tedious, subjective, and error prone. In this paper, procedures for characterizing the behavior of laminated unidirectional composites (UDCs) are explained. First, laboratory tests are conducted to obtain the orthotropic material properties of a commonly used composite, IM7-8552. The obtained data are used in the MAT_213 model in LS-DYNA. Second, fracture-related tests, i.e., double-cantilever beam (DCB) and end-notched flexure (ENF) tests, are conducted to obtain the load-displacement responses. Finally, an inverse analysis approach is used by combining response surface methodology (RSM) and gradient-based numerical optimization to find the optimal values of the traction-separation law (TSL) parameters to build the constitutive model for modeling delamination. The developed cohesive zone element (CZE) model is then validated using the experimental results of a quasi-isotropic tension test. It is shown that the overall process of analyzing the experimental data and building a finite-element model is simpler, and the results from the validation test indicate that the developed methodology can yield accurate predictions.
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      Improving Delamination Modeling via Inverse Analysis

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    http://yetl.yabesh.ir/yetl1/handle/yetl/4298577
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    contributor authorAshutosh Maurya
    contributor authorMohammed Raihan
    contributor authorSubramaniam Rajan
    date accessioned2024-12-24T10:15:17Z
    date available2024-12-24T10:15:17Z
    date copyright9/1/2024 12:00:00 AM
    date issued2024
    identifier otherJAEEEZ.ASENG-5613.pdf
    identifier urihttp://yetl.yabesh.ir/yetl1/handle/yetl/4298577
    description abstractDeveloping constitutive models that can be used to model composite structural systems subjected to impact loads where modeling damage, failure, and delamination are critical is a challenging task. Often processing experimental data to develop the composite material model and, especially, the delamination model can be tedious, subjective, and error prone. In this paper, procedures for characterizing the behavior of laminated unidirectional composites (UDCs) are explained. First, laboratory tests are conducted to obtain the orthotropic material properties of a commonly used composite, IM7-8552. The obtained data are used in the MAT_213 model in LS-DYNA. Second, fracture-related tests, i.e., double-cantilever beam (DCB) and end-notched flexure (ENF) tests, are conducted to obtain the load-displacement responses. Finally, an inverse analysis approach is used by combining response surface methodology (RSM) and gradient-based numerical optimization to find the optimal values of the traction-separation law (TSL) parameters to build the constitutive model for modeling delamination. The developed cohesive zone element (CZE) model is then validated using the experimental results of a quasi-isotropic tension test. It is shown that the overall process of analyzing the experimental data and building a finite-element model is simpler, and the results from the validation test indicate that the developed methodology can yield accurate predictions.
    publisherAmerican Society of Civil Engineers
    titleImproving Delamination Modeling via Inverse Analysis
    typeJournal Article
    journal volume37
    journal issue5
    journal titleJournal of Aerospace Engineering
    identifier doi10.1061/JAEEEZ.ASENG-5613
    journal fristpage04024056-1
    journal lastpage04024056-16
    page16
    treeJournal of Aerospace Engineering:;2024:;Volume ( 037 ):;issue: 005
    contenttypeFulltext
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