Email this article Research on Nonlinear Deformation and Stability of an Advanced Aircraft Fuselage Composite Section under Pure Bending
- Authors: Belov V.K.1, Zheleznov L.P.1, Ognyanova T.S.1
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Affiliations:
- S. A. Chaplygin Aeronautical Research Institute (SibNIA)
- Issue: Vol 60, No 4 (2017)
- Pages: 514-522
- Section: Structural Mechanics and Strength of Flight Vehicles
- URL: https://journal-vniispk.ru/1068-7998/article/view/230272
- DOI: https://doi.org/10.3103/S1068799817040067
- ID: 230272
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Abstract
The finite element algorithm developed by the authors has been used for solving the strength and stability problems of shells. The effect of deformation nonlinearity, stiffness of stringer set, shell thickness on critical loads has been determined.
About the authors
V. K. Belov
S. A. Chaplygin Aeronautical Research Institute (SibNIA)
Email: to19@list.ru
Russian Federation, ul. Polzunova 21, Novosibirsk, 630051
L. P. Zheleznov
S. A. Chaplygin Aeronautical Research Institute (SibNIA)
Email: to19@list.ru
Russian Federation, ul. Polzunova 21, Novosibirsk, 630051
T. S. Ognyanova
S. A. Chaplygin Aeronautical Research Institute (SibNIA)
Author for correspondence.
Email: to19@list.ru
Russian Federation, ul. Polzunova 21, Novosibirsk, 630051
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