Open AccessAeroelastic stability of a shell supported by a cylinder with a hole of linearly varying radius
Author(s) -
M. A. Konopelchev,
В. Н. Бакулин,
A. Ya. Nedbai
Publication year - 2019
Publication title -
journal of physics. conference series
Language(s) - English
Resource type - Journals
SCImago Journal Rank - 0.21
H-Index - 85
eISSN - 1742-6596
pISSN - 1742-6588
DOI - 10.1088/1742-6596/1392/1/012010
Subject(s) - cylinder , aeroelasticity , shell (structure) , radius , choked flow , elasticity (physics) , physics , supersonic speed , mathematics , mechanics , mathematical analysis , classical mechanics , materials science , geometry , aerodynamics , composite material , thermodynamics , computer security , computer science
The aeroelastic stability of a shell supported by an elastic cylinder of varying thickness with the outer surface exposed to supersonic gas flow is studied. The supporting cylinder is considered as an elastic foundation, whose bedding value is determined from the equations of the three-dimensional theory of elasticity. The solution is obtained by the BubnovGalerkin method in the form of a trigonometric series in the axial coordinate. The characteristic equation is approximated by the Lagrange polynomial, whose stability is investigated with the use of the Routh-Hurwitz criterion. The dependences of the critical flow velocity on the length of the cylinder section with the tapered hole are shown for various values of the axial force, the damping decrement, and the shell thickness.