In this research, behavior of a cylindrical sandwich panel with the flexible core in different boundary conditions, under the influence of follower force are studied. For this purpose, using the theory of the first-order shear deformation, and the principle of Hamilton, the governing equations have been extracted and by using generalized differential quadrature method (GDQM) are solved. The obtained results indicate that by considering simplicity of present method compared to the other methods in the analysis of stability problems of the cylindrical sandwich panel, the present results have the acceptable accuracy. Also, the results review show that the flutter phenomenon occurs in the free and clamp boundary conditions and for other boundary conditions only the divergence phenomenon or static buckling occurs. Another significant result is that increasing the number of composite layers, makes the flutter phenomenon in the cylindrical sandwich panel with the flexible core occurs later.
Pourmoayed, A., Malekzadeh Fard, K., & Shahravi, M. (2018). Flatter analysis of cylindrical sandwich panel under follower force
using generalized differential quadrature method. Journal of Aeronautical Engineering, 20(1), 49-61.
MLA
Alireza Pourmoayed; Keramat Malekzadeh Fard; Morteza Shahravi. "Flatter analysis of cylindrical sandwich panel under follower force
using generalized differential quadrature method". Journal of Aeronautical Engineering, 20, 1, 2018, 49-61.
HARVARD
Pourmoayed, A., Malekzadeh Fard, K., Shahravi, M. (2018). 'Flatter analysis of cylindrical sandwich panel under follower force
using generalized differential quadrature method', Journal of Aeronautical Engineering, 20(1), pp. 49-61.
VANCOUVER
Pourmoayed, A., Malekzadeh Fard, K., Shahravi, M. Flatter analysis of cylindrical sandwich panel under follower force
using generalized differential quadrature method. Journal of Aeronautical Engineering, 2018; 20(1): 49-61.
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