Мақаланы E-mail арқылы жіберу Research on Nonlinear Deformation and Stability of an Advanced Aircraft Fuselage Composite Section under Pure Bending
- Авторлар: Belov V.1, Zheleznov L.1, Ognyanova T.1
-
Мекемелер:
- S. A. Chaplygin Aeronautical Research Institute (SibNIA)
- Шығарылым: Том 60, № 4 (2017)
- Беттер: 514-522
- Бөлім: 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
Дәйексөз келтіру
Ашық рұқсат
Рұқсат берілді
Тек жазылушылар үшін
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.
Авторлар туралы
V. Belov
S. A. Chaplygin Aeronautical Research Institute (SibNIA)
Email: to19@list.ru
Ресей, ul. Polzunova 21, Novosibirsk, 630051
L. Zheleznov
S. A. Chaplygin Aeronautical Research Institute (SibNIA)
Email: to19@list.ru
Ресей, ul. Polzunova 21, Novosibirsk, 630051
T. Ognyanova
S. A. Chaplygin Aeronautical Research Institute (SibNIA)
Хат алмасуға жауапты Автор.
Email: to19@list.ru
Ресей, ul. Polzunova 21, Novosibirsk, 630051
