Research on Nonlinear Deformation and Stability of an Advanced Aircraft Fuselage Composite Section under Pure Bending.

Autor: Belov, V. K., Zheleznov, L. P., Ognyanova, T. S.
Zdroj: Russian Aeronautics; Oct2017, Vol. 60 Issue 4, p514-522, 9p
Abstrakt: 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. [ABSTRACT FROM AUTHOR]
Databáze: Complementary Index
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