• Login
    View Item 
    •   Shocker Open Access Repository Home
    • Office of Research
    • NIAR: National Institute for Aviation Research
    • NIAR Research Publications
    • View Item
    •   Shocker Open Access Repository Home
    • Office of Research
    • NIAR: National Institute for Aviation Research
    • NIAR Research Publications
    • View Item
    JavaScript is disabled for your browser. Some features of this site may not work without it.

    Progressive damage and failure analysis of bonded composite joints at high energy dynamic impacts

    Date
    2019-09
    Author
    Bhasin, Akhil
    Keshavanarayana, Suresh R.
    Gomez Valbuena, Luis M.
    Kona Ravi, Aswini
    Justusson, Brian P.
    Olivares, Gerardo
    Metadata
    Show full item record
    Citation
    Bhasin, Akhil; Keshavanarayana, Suresh R.; Gomez, Luis; Kona Ravi, Aswini; Justusson, Brian P.; Olivares, Gerardo. 2019. Progressive damage and failure analysis of bonded composite joints at high energy dynamic impacts. 34th Technical Conference of the American Society for Composites, ASC 2019
    Abstract
    Both wing and fuselage structures utilize bonded composite joints for structural efficiency in modern commercial and military aircraft. To ensure compliance with certification requirements mechanical fasteners are typically used as a failsafe mechanism for appropriate strength in the event of complete stiffener disbond. However, the use of fasteners decreases the structural efficiency of the structure by adding weight. This establishes the requirement to better exploit the efficiency of bonded structures and fully understand the failure behavior of adhesively bonded composite structures, particularly when subjected to elevated loading rates due to high energy dynamic impacts (HEDI). For this reason, the NASA Advanced Composite Consortium (ACC) HEDI team developed an experimentation and numerical modeling program for high rate loading of composite joints [1] [2]. In the present work, the response of adhesively bonded composite joints subjected to elevated loading rates is studied numerically and validated against experimental results. Due to dynamic considerations of experiments, the idea of wedge insert [3] was extended to use with Split Hopkinson Pressure Bar (SHPB) testing techniques. Mode-I and Mode-II test configurations were simulated to evaluate the capability of two continuum damage material (CDM) models in LS-DYNA, namely MAT162 and MAT261 [4]. Three different levels of fidelity were considered to investigate the level of detail required to numerically predict the failure behavior and the results from high fidelity analysis are presented.
    Description
    Click on the DOI link to access the article (may not be free.
    URI
    https://doi.org/10.12783/asc34/31266
    http://hdl.handle.net/10057/17084
    Collections
    • NIAR Research Publications

    Browse

    All of Shocker Open Access RepositoryCommunities & CollectionsBy Issue DateAuthorsTitlesSubjectsBy TypeThis CollectionBy Issue DateAuthorsTitlesSubjectsBy Type

    My Account

    LoginRegister

    Statistics

    Most Popular ItemsStatistics by CountryMost Popular Authors

    DSpace software copyright © 2002-2022  DuraSpace
    DSpace Express is a service operated by 
    Atmire NV