Nonlinear Deformation and Stability of the Aircraft Fuselage Composite Section under Pure Bending

被引：0
作者：
Zheleznov L.P. [1 ]
Ser’eznov A.N. [1 ]
机构：
[1] Chaplygin Aeronautical Research Institute (SibNIA), ul. Polzunova 21, Novosibirsk
来源：
Russian Aeronautics | 2021年 / 64卷 / 03期
关键词：
cylindrical composite shells; discrete reinforcement; finite element method; nonlinear deformation; stability;
D O I：
10.3103/S106879982103003X
中图分类号：
学科分类号：
摘要：
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. © 2021, Allerton Press, Inc.
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页码：385 / 393
页数：8
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