Research on Nonlinear Deformation and Stability of an Advanced Aircraft Fuselage Composite Section under Pure Bending
- Авторы: Belov V.K.1, Zheleznov L.P.1, Ognyanova T.S.1
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Учреждения:
- S. A. Chaplygin Aeronautical Research Institute (SibNIA)
- Выпуск: Том 60, № 4 (2017)
- Страницы: 514-522
- Раздел: 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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Аннотация
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.
Об авторах
V. Belov
S. A. Chaplygin Aeronautical Research Institute (SibNIA)
Email: to19@list.ru
Россия, ul. Polzunova 21, Novosibirsk, 630051
L. Zheleznov
S. A. Chaplygin Aeronautical Research Institute (SibNIA)
Email: to19@list.ru
Россия, ul. Polzunova 21, Novosibirsk, 630051
T. Ognyanova
S. A. Chaplygin Aeronautical Research Institute (SibNIA)
Автор, ответственный за переписку.
Email: to19@list.ru
Россия, ul. Polzunova 21, Novosibirsk, 630051
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