Abstract
The paper presents the research results obtained on the basis of a technique that implements the finite element method for solving the problems of strength and stability of discrete-reinforced cylindrical shells made of the composite material, taking into account the momentness and nonlinearity of their subcritical stress-strain state. The stability under pure bending of a reinforced aircraft fuselage section made of composite material was investigated. The effect of deformation nonlinearity, stiffness of stringer fraiming, and shell thickness on critical loads of the shell stability loss is determined.
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Translated from Izvestiya Vysshikh Uchebnykh Zavedenii, Aviatsionnaya Tekhnika, 2021, No. 3, pp. 22 - 30.
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Zheleznov, L.P., Ser’eznov, A.N. Nonlinear Deformation and Stability of the Aircraft Fuselage Composite Section under Pure Bending. Russ. Aeronaut. 64, 385–393 (2021). https://doi.org/10.3103/S106879982103003X
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DOI: https://doi.org/10.3103/S106879982103003X