Investigation of Nonlinear Deformation and Stability of a Composite Shell under Pure Bending and Internal Pressure
L. P. Zheleznov, A. N. Ser'eznov
Chaplygin Siberian Scientific Research Institute of Aviation, Novosibirsk, 630051, Russia
Keywords: cylindrical composite shells, discrete reinforcements, nonlinear deformation, stability, finite element method
Abstract
The finite element method is used to obtain solutions to problems of strength and stability of reinforced cylindrical shells made of composite material with account for the momentum and nonlinearity of their subcritical stress-strain state. The stability of a reinforced aircraft fuselage compartment made of composite material is studied under pure bending and internal pressure loading. The effect of deformation nonlinearity, stringer stiffness, and shell thickness on critical loads at which shell buckling occurs is studied.
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