Static Analysis of Infinite Laminated Cylindrical Shell Panel
This paper presents an approximate three-dimensional elasticity solution for an infinitely long, cross-ply laminated circular cylindrical shell panel with simply supported boundary conditions, subjected to an arbitrary discontinuous transverse loading. The solution is based on the principal assumption that the ratio of the thickness of the lamina to its middle surface radius is negligible compared to unity. The validity of this assumption and the range of application of this approximate solution have been established through a comparison with an exact solution. Results of classical and first-order shear deformation shell theories have been compared with the results of the present solution to bring out the accuracy of these theories. It is also shown that for very shallow shell panels the definition of a thin shell should be based on the ratio of thickness to chord width rather than the ratio of thickness to mean radius.
K. Chandrashekhara and K. S. Rao, "Static Analysis of Infinite Laminated Cylindrical Shell Panel," Journal of Aerospace Engineering, American Society of Civil Engineers (ASCE), Jan 1998.
The definitive version is available at https://doi.org/10.1061/(ASCE)0893-1321(1998)11:1(1)
Mechanical and Aerospace Engineering
International Standard Serial Number (ISSN)
Article - Journal
© 1998 American Society of Civil Engineers (ASCE), All rights reserved.
01 Jan 1998