The aeroelastic stability of simply supported, circular cylindrical shells in supersonic Row is investigated. Non-linearities caused by large-amplitude shell motion are considered by using the Donnell nonlinear shallow-shell theory, and the effect of viscous structural damping is taken into account, Two different in-plane constraints are applied to the shell edges: zero axial force and zero axial displacement; the other boundary conditions are those for simply supported shells. Linear piston theory is applied to describe the fluid-structure interaction by using two different formulations, taking into account or neglecting the curvature correction term. The system is discretized by Galerkin projections and is investigated by using a model involving seven degrees of freedom, allowing for traveling-wave flutter of the shell and shell axisymmetric contraction. Results show that the system loses stability by standing-wave flutter through supercritical bifurcation; however, traveling-wave flutter appears with a very small increment of the freestream static pressure that is used as the bifurcation parameter, A very good agreement between theoretical and existing experimental data has been found for flutter amplitudes. The influence of internal static pressure has also been studied.
Nonlinear supersonic flutter of circular cylindrical shells / M., Amabili; Pellicano, Francesco. - In: AIAA JOURNAL. - ISSN 0001-1452. - STAMPA. - 39(2001), pp. 564-573.
|Data di pubblicazione:||2001|
|Titolo:||Nonlinear supersonic flutter of circular cylindrical shells|
|Autore/i:||M., Amabili; Pellicano, Francesco|
|Codice identificativo ISI:||WOS:000167794200002|
|Codice identificativo Scopus:||2-s2.0-0035311886|
|Citazione:||Nonlinear supersonic flutter of circular cylindrical shells / M., Amabili; Pellicano, Francesco. - In: AIAA JOURNAL. - ISSN 0001-1452. - STAMPA. - 39(2001), pp. 564-573.|
|Tipologia||Articolo su rivista|
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