Nonlinear Thermal Dynamic Analysis of Graphite/Aluminum Composite Plates
Because of the increased application of composite materials in high-temperature environments, the thermoelastic analysis of laminated composite structures is important. Many researchers have applied the classical lamination theory to analyze laminated plates under thermomechanical loading, which neglects shear deformation effects. The transverse shear deformation effects are not negligible as the ratios of inplane elastic modulus to transverse shear modulus are relatively large for fiber-reinforced composite laminates. The application of first-order shear deformation theory for the thermoelastic analysis of laminated plates has been reported by only a few investigators. Reddy and Hsu have considered the thermal bending of laminated plates. The analytical and finite element solutions for the thermal bucking of laminated plates have been reported by Tauchert and Chandrashekara, respectively. However, the first-order shear deformation theory, based on the assumption of constant distribution of transverse shear through the thickness, requires a shear correction factor to account for the parabolic shear strain distribution. Higher order theories have been proposed which eliminate the need for a shear correction factor. In the present work, nonlinear dynamic analysis of laminated plates subjected to rapid heating is investigated using a higher order shear deformation theory. A C(sup 0) finite element model with seven degrees of freedom per node is implmented and numerical results are presented for laminated graphite/aluminum plates.
R. Tenneti and K. Chandrashekhara, "Nonlinear Thermal Dynamic Analysis of Graphite/Aluminum Composite Plates," AIAA Journal, American Institute of Aeronautics and Astronautics (AIAA), Jan 1994.
The definitive version is available at https://doi.org/10.2514/3.12197
Mechanical and Aerospace Engineering
International Standard Serial Number (ISSN)
Article - Journal
© 1994 American Institute of Aeronautics and Astronautics (AIAA), All rights reserved.
01 Jan 1994