Finite element analysis of the panel flutter of stiffened shallow shells

The aeroelastic stability of flat plates and shallow cylindrical shells stiffened with stringers is investigated. In the case of a curved panel, the supersonic gas flow is parallel to its generatrix. A mathematical formulation of the dynamics problem is based on the variational principle of virtual...

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Bibliographic Details
Published in:Continuum mechanics and thermodynamics 2023-07, Vol.35 (4), p.1275-1290
Main Authors: Bochkarev, Sergey A., Lekomtsev, Sergey V., Matveenko, Valery P.
Format: Article
Language:English
Subjects:
Aeroelastic stability
Analysis
Boundary conditions
Classical and Continuum Physics
Curved panels
Cylindrical shells
Eigenvalues
Engineering Thermodynamics
External pressure
Finite element method
Flat plates
Flow control
Gas flow
Heat and Mass Transfer
Original Article
Panel flutter
Physics
Physics and Astronomy
Shallow shells
Shell stability
Stability analysis
Stringers
Structural Materials
Superposition (mathematics)
Theoretical and Applied Mechanics
Vibration
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Summary:The aeroelastic stability of flat plates and shallow cylindrical shells stiffened with stringers is investigated. In the case of a curved panel, the supersonic gas flow is parallel to its generatrix. A mathematical formulation of the dynamics problem is based on the variational principle of virtual displacements taking into account the work done by the inertial forces and aerodynamic pressure of the external supersonic gas flow determined according to the quasi-static aerodynamic theory. The solution is found by the finite element method in a three-dimensional formulation using the mode-superposition technique. The estimation of the shell stability is based on the analysis of complex eigenvalues of the system of equations calculated under gradually increasing aerodynamic pressure. The validity of the obtained results is confirmed by comparing them with the known solutions to a number of relevant problems. Numerical examples are used to analyze in detail the influence of the curvature ratio, the boundary conditions specified at the edges of the shallow shell, and the number of stringers on the boundary of stability loss. It is demonstrated that with an optimal arrangement of reinforcing elements, it is possible to achieve a significant increase in the critical parameters of the flutter.
ISSN:0935-1175
1432-0959
DOI:10.1007/s00161-022-01123-6