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    A Computationally Efficient C0 Continuous Finite-Element Model for Static and Free Vibration Analysis of Delaminated Composite Plates in a Nonpolynomial Axiomatic Framework

    Source: Journal of Aerospace Engineering:;2025:;Volume ( 038 ):;issue: 001::page 04024114-1
    Author:
    Abhiraj Sinha
    ,
    Abhijeet Babar
    ,
    Nitin Bhardwaj
    ,
    Rosalin Sahoo
    ,
    S. Mandal
    DOI: 10.1061/JAEEEZ.ASENG-5703
    Publisher: American Society of Civil Engineers
    Abstract: This study examines the bending and free vibration behaviors of delaminated composite plates using inverse hyperbolic shear deformation theory (IHSDT). This theory incorporates a nonlinear shear stress distribution and inherently satisfies the traction-free boundary conditions at the top and bottom surfaces, thus omitting the shear correction factor. The approach employed is based on the finite element method utilizing eight-noded isoparametric elements. This study examines how the size, location, and stacking sequence of delaminations impact the flexural properties of the plates. Furthermore, the research delves into other geometric parameters, including delamination thickness and shape, to know their influence. The primary objective of the study is to determine the most effective configurations for mitigating the adverse consequences of delaminations. To develop design guidelines and optimization techniques for structurally strong and efficient composite structures, the results provide valuable insights into the static and free vibration behavior of delaminated composite plates. Overall, this study advances the field and enhances design practices by conducting a complete analysis of the static and dynamic behavior of delaminated composite plates.
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      A Computationally Efficient C0 Continuous Finite-Element Model for Static and Free Vibration Analysis of Delaminated Composite Plates in a Nonpolynomial Axiomatic Framework

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    http://yetl.yabesh.ir/yetl1/handle/yetl/4307032
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    contributor authorAbhiraj Sinha
    contributor authorAbhijeet Babar
    contributor authorNitin Bhardwaj
    contributor authorRosalin Sahoo
    contributor authorS. Mandal
    date accessioned2025-08-17T22:30:33Z
    date available2025-08-17T22:30:33Z
    date copyright1/1/2025 12:00:00 AM
    date issued2025
    identifier otherJAEEEZ.ASENG-5703.pdf
    identifier urihttp://yetl.yabesh.ir/yetl1/handle/yetl/4307032
    description abstractThis study examines the bending and free vibration behaviors of delaminated composite plates using inverse hyperbolic shear deformation theory (IHSDT). This theory incorporates a nonlinear shear stress distribution and inherently satisfies the traction-free boundary conditions at the top and bottom surfaces, thus omitting the shear correction factor. The approach employed is based on the finite element method utilizing eight-noded isoparametric elements. This study examines how the size, location, and stacking sequence of delaminations impact the flexural properties of the plates. Furthermore, the research delves into other geometric parameters, including delamination thickness and shape, to know their influence. The primary objective of the study is to determine the most effective configurations for mitigating the adverse consequences of delaminations. To develop design guidelines and optimization techniques for structurally strong and efficient composite structures, the results provide valuable insights into the static and free vibration behavior of delaminated composite plates. Overall, this study advances the field and enhances design practices by conducting a complete analysis of the static and dynamic behavior of delaminated composite plates.
    publisherAmerican Society of Civil Engineers
    titleA Computationally Efficient C0 Continuous Finite-Element Model for Static and Free Vibration Analysis of Delaminated Composite Plates in a Nonpolynomial Axiomatic Framework
    typeJournal Article
    journal volume38
    journal issue1
    journal titleJournal of Aerospace Engineering
    identifier doi10.1061/JAEEEZ.ASENG-5703
    journal fristpage04024114-1
    journal lastpage04024114-14
    page14
    treeJournal of Aerospace Engineering:;2025:;Volume ( 038 ):;issue: 001
    contenttypeFulltext
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