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dc.contributor.authorBhasin, Akhil
dc.contributor.authorKeshavanarayana, Suresh R.
dc.contributor.authorGomez Valbuena, Luis M.
dc.contributor.authorKona Ravi, Aswini
dc.contributor.authorJustusson, Brian P.
dc.contributor.authorOlivares, Gerardo
dc.date.accessioned2020-02-21T16:04:48Z
dc.date.available2020-02-21T16:04:48Z
dc.date.issued2019-09
dc.identifier.citationBhasin, 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 2019en_US
dc.identifier.isbn978-160595602-2
dc.identifier.urihttps://doi.org/10.12783/asc34/31266
dc.identifier.urihttp://hdl.handle.net/10057/17084
dc.descriptionClick on the DOI link to access the article (may not be free.en_US
dc.description.abstractBoth 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.en_US
dc.description.sponsorshipNASA under Award Nos. NNL09AA00A and 80LARC17C0004.en_US
dc.language.isoen_USen_US
dc.publisherDEStech Publicationsen_US
dc.relation.ispartofseries34th Technical Conference of the American Society for Composites, ASC;2019
dc.subjectAdhesivesen_US
dc.subjectDynamicsen_US
dc.subjectFuselagesen_US
dc.subjectJoints (structural components)en_US
dc.subjectMechanical testingen_US
dc.subjectNASAen_US
dc.titleProgressive damage and failure analysis of bonded composite joints at high energy dynamic impactsen_US
dc.typeConference paperen_US
dc.rights.holder© 2019 by DEStech Publications, Inc. and American Society for Composites. All rights reserveden_US


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