Stability of a Non-Circular Composite Shell under Axial Compression and Nonlinear Deformation
L. P. Zheleznov
Chaplygin Siberian Scientific Research Institute of Aviation, Novosibirsk, Russia
Keywords: shell, polymer composite material, nonlinearity, stability, finite element method, compression
Abstract
The results of the study of the strength and stability of oval composite cylindrical shells under axial compression are presented. The geometrically nonlinear problem for the shell is solved using the finite element method. The geometric dimensions of the shell are close those of fuselages of modern passenger aircrafts. Another phenomenon described in this paper is the effect of the cross-sectional out-of-roundness of the shell, the nonlinearity of the initial stress-strain state, and the stacking of monolayers by thickness on the critical loads and weight efficiency of composite and metal shells.
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