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    Simplified Analysis of Negative Shear Lag in Laminated Composite Cantilever Beam

    Source: Journal of Aerospace Engineering:;2020:;Volume ( 033 ):;issue: 001
    Author:
    Gyani Jail Singh
    ,
    Sasankasekhar Mandal
    ,
    Rajesh Kumar
    ,
    Veerendra Kumar
    DOI: 10.1061/(ASCE)AS.1943-5525.0001100
    Publisher: ASCE
    Abstract: In the present study, a composite cantilever beam subjected to shear loading has been analyzed. A simplified procedure is presented to examine the composite cantilever beam. The governing differential equations and boundary conditions are established by applying the principle of minimum potential energy, and solutions to the differential equation are given. A very simple and convenient formula to calculate the bending stresses consisting of shear lag in a composite cantilever beam is derived, which has a similar form as that of the bending stress in the elementary beam theory (EBT). A numerical example is illustrated to demonstrate the simplicity and accuracy of the proposed simplified method. For EsIs/EoIo=0.731, the stress factor (σx/σ), i.e., the ratio of actual flange stress to the stress calculated by EBT in the central line of the cover sheet at the clamped end, is computed as the following: 1.120, corresponding to the uniformly distributed load; 1.067, corresponding to the point load; 1.165, corresponding to the uniformly varied load increasing toward the support and 1.102 corresponding to the uniformly varied load decreasing toward the support. The results obtained by the simplified method have been verified by finite-element analysis (FEA). Further, the present methodology is compared with the Reissner box beam methodology. The theoretical results are found to compare well with test results and literature.
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      Simplified Analysis of Negative Shear Lag in Laminated Composite Cantilever Beam

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    http://yetl.yabesh.ir/yetl1/handle/yetl/4266351
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    • Journal of Aerospace Engineering

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    contributor authorGyani Jail Singh
    contributor authorSasankasekhar Mandal
    contributor authorRajesh Kumar
    contributor authorVeerendra Kumar
    date accessioned2022-01-30T20:00:17Z
    date available2022-01-30T20:00:17Z
    date issued2020
    identifier other%28ASCE%29AS.1943-5525.0001100.pdf
    identifier urihttp://yetl.yabesh.ir/yetl1/handle/yetl/4266351
    description abstractIn the present study, a composite cantilever beam subjected to shear loading has been analyzed. A simplified procedure is presented to examine the composite cantilever beam. The governing differential equations and boundary conditions are established by applying the principle of minimum potential energy, and solutions to the differential equation are given. A very simple and convenient formula to calculate the bending stresses consisting of shear lag in a composite cantilever beam is derived, which has a similar form as that of the bending stress in the elementary beam theory (EBT). A numerical example is illustrated to demonstrate the simplicity and accuracy of the proposed simplified method. For EsIs/EoIo=0.731, the stress factor (σx/σ), i.e., the ratio of actual flange stress to the stress calculated by EBT in the central line of the cover sheet at the clamped end, is computed as the following: 1.120, corresponding to the uniformly distributed load; 1.067, corresponding to the point load; 1.165, corresponding to the uniformly varied load increasing toward the support and 1.102 corresponding to the uniformly varied load decreasing toward the support. The results obtained by the simplified method have been verified by finite-element analysis (FEA). Further, the present methodology is compared with the Reissner box beam methodology. The theoretical results are found to compare well with test results and literature.
    publisherASCE
    titleSimplified Analysis of Negative Shear Lag in Laminated Composite Cantilever Beam
    typeJournal Paper
    journal volume33
    journal issue1
    journal titleJournal of Aerospace Engineering
    identifier doi10.1061/(ASCE)AS.1943-5525.0001100
    page04019103
    treeJournal of Aerospace Engineering:;2020:;Volume ( 033 ):;issue: 001
    contenttypeFulltext
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