Enviar artigo por via de e-mail Research on Nonlinear Deformation and Stability of an Advanced Aircraft Fuselage Composite Section under Pure Bending
- Autores: Belov V.K.1, Zheleznov L.P.1, Ognyanova T.S.1
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Afiliações:
- S. A. Chaplygin Aeronautical Research Institute (SibNIA)
- Edição: Volume 60, Nº 4 (2017)
- Páginas: 514-522
- Seção: Structural Mechanics and Strength of Flight Vehicles
- URL: https://journals.rcsi.science/1068-7998/article/view/230272
- DOI: https://doi.org/10.3103/S1068799817040067
- ID: 230272
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Resumo
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.
Sobre autores
V. Belov
S. A. Chaplygin Aeronautical Research Institute (SibNIA)
Email: to19@list.ru
Rússia, ul. Polzunova 21, Novosibirsk, 630051
L. Zheleznov
S. A. Chaplygin Aeronautical Research Institute (SibNIA)
Email: to19@list.ru
Rússia, ul. Polzunova 21, Novosibirsk, 630051
T. Ognyanova
S. A. Chaplygin Aeronautical Research Institute (SibNIA)
Autor responsável pela correspondência
Email: to19@list.ru
Rússia, ul. Polzunova 21, Novosibirsk, 630051
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