ARTICLE
Free vibration and buckling analysis of composite laminated shells using the refined zigzag theory
1
Department of Aeronautics and Astronautics, Shenyang Aerospace University, Shenyang, China
2
College of Aerospace Science and Engineering, National University of Defense Technology, Changsha, China
3
Beijing Institute of Astronautical Systems Engineering, Beijing, China
4
Department of Mechanics, Huazhong University of Science and Technology, Wuhan, China
Submission date: 2022-05-20
Acceptance date: 2022-05-25
Online publication date: 2022-06-17
Publication date: 2022-07-30
Corresponding author
Journal of Theoretical and Applied Mechanics 2022;60(3):435-448
KEYWORDS
TOPICS
ABSTRACT
In this study, a new composite laminated shell model is proposed for free vibration and
stability analysis based on the refined zigzag theory (RZT). In contrast to the published
shell models based on the first-order shear deformation theory (FSDT), piecewise-linear
zigzag functions are utilized to provide a more realistic representation of deformation states
of a transverse shear-flexible shell. In the present formulation, the governing equations and
boundary conditions of composite laminated shells are established by d’Alembert’s principle
to obtain natural frequencies and critical buckling loadings. In order to evaluate the effectiveness
and performance of the present new model for composite laminated shells, examples
of free vibration and buckling analysis are carried out for cylindrical and spherical shells involving
different lamination schemes and design parameters. The results are compared with
the three dimensional (3D) exact, first-order and some high-order solutions in the literature.
Numerical results show that the present model not only has high accuracy but also has
superior computational efficiency in comparison with high-order models, such that it may
show a great potential in engineering applications.
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| eISSN: | 2543-6309 |
| ISSN: | 1429-2955 |
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