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An Investigation of the Accuracy of FEM Analysis of a Graphite Epoxy Box Beam
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English
Abstract
A carbon fiber-epoxy wing box was constructed in order to study the behavior of a stressed-skin wing structure with anisotropic sandwich skins. Two wing skins, two spars, and three ribs made up the structure. The spars were designed to act primarily as shear webs so that the bending load in the structure would be reacted mainly by tension and compression in the skins. Linear, buckling, and nonlinear NASTRAN finite element solution sequences were implemented in the analysis of the structure. The structure was loaded as a cantilever beam and strain and deflection measurements were recorded. The finite element nonlinear analysis accurately modeled stiffness, but results for strains at a point were not as accurate.
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Citation
Baldwin, J. and McWhorter, J., "An Investigation of the Accuracy of FEM Analysis of a Graphite Epoxy Box Beam," SAE Technical Paper 931221, 1993, https://doi.org/10.4271/931221.Also In
References
- Baldwin J.D. “The Design, Construction, Analysis, and Testing of an Elastically Tailored Carbon Fiber/Epoxy Wing Box Structure,” Thesis Department of Aerospace Engineering, Mississippi State University 1992
- Sherrouse M.A. “Analysis and Testing of Composite Sandwich Shell Aircraft Structures,” Thesis Department of Aerospace Engineering, Mississippi State University 1990
- Sherrouse M.A. McWhorter J.C. III “Analysis and Testing of a Composite Sandwich Shell Horizontal Tail,” Testing and Design Tenth ASTM STP 1120 1992