Abstract
The aeroelastic stability of a medium length cantilever cylindrical shell stiffened by an edge ring with the outer surface exposed to supersonic gas flow is investigated. The shell motion is described by the equations of the semi-membrane theory for laminated shells and considered with various end conditions. The dependences of the critical flutter speed on the dimensions of the ring cross-section, the value of the structural damping coefficient, the flow parameters, and the type of boundary conditions are obtained.
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Original Russian Text © V.N. Bakulin, M.A. Konopel’chev, A.Ya. Nedbai, 2018, published in Izvestiya Vysshikh Uchebnykh Zavedenii, Aviatsionnaya Tekhnika, 2018, No. 4, pp. 14–19.
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Bakulin, V.N., Konopel’chev, M.A. & Nedbai, A.Y. Flutter of a Laminated Cantilever Cylindrical Shell with a Ring-Stiffened Edge. Russ. Aeronaut. 61, 517–523 (2018). https://doi.org/10.3103/S1068799818040037
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DOI: https://doi.org/10.3103/S1068799818040037