Simplified Analysis of Negative Shear Lag in Laminated Composite Cantilever Beam
Publication: Journal of Aerospace Engineering
Volume 33, Issue 1
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 , the stress factor (), 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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Data Availability Statement
All data, models, and code generated or used during the study appear in the submitted article.
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Published In
Journal of Aerospace Engineering
Volume 33 • Issue 1 • January 2020
Copyright
©2019 American Society of Civil Engineers.
History
Received: Feb 3, 2018
Accepted: Aug 7, 2019
Published online: Sep 29, 2019
Published in print: Jan 1, 2020
Discussion open until: Feb 29, 2020
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