Nonlinear Deformation and Stability of a Noncircular Cylindrical Shell Under Combined Loading with Bending and Twisting Moments
- 作者: Belov V.1, Zheleznov L.1, Ognyanova T.1
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隶属关系:
- Siberian Aeronautic Research Institute (SibNIA) named after S. A. Chaplygin
- 期: 卷 59, 编号 2 (2018)
- 页面: 352-358
- 栏目: Article
- URL: https://journals.rcsi.science/0021-8944/article/view/161053
- DOI: https://doi.org/10.1134/S0021894418020190
- ID: 161053
如何引用文章
详细
A previously developed technique is used to solve problems of strength and stability of discretely reinforced noncircular cylindrical shells made of a composite material with allowance for the moments and nonlinearity of their subcritical stress–strain state. Stability of a reinforced bay of the aircraft fuselage made of a composite material under combined loading with bending and twisting moments is studied. The effects of straining nonlinearity, stiffness of longitudinal ribs, and shell thickness on the critical loads that induce shell buckling are analyzed.
作者简介
V. Belov
Siberian Aeronautic Research Institute (SibNIA) named after S. A. Chaplygin
编辑信件的主要联系方式.
Email: sibnia@sibnia.ru
俄罗斯联邦, Novosibirsk, 630000
L. Zheleznov
Siberian Aeronautic Research Institute (SibNIA) named after S. A. Chaplygin
Email: sibnia@sibnia.ru
俄罗斯联邦, Novosibirsk, 630000
T. Ognyanova
Siberian Aeronautic Research Institute (SibNIA) named after S. A. Chaplygin
Email: sibnia@sibnia.ru
俄罗斯联邦, Novosibirsk, 630000