Thermoelastic stability of closed cylindrical shell in supersonic gas flow

Thermoelastic Response of Closed Cylindrical Shells in a Supersonic Gas Flow

“…The stationary temperature field T which is inhomogeneous over the thickness of the shell Θ 0, leads to the shell buckling (with a deflection w T (x) and a longitudinal displacement u T (x)) and, as a result, an additional aeroelastic pressure appears. We accept this buckled state as unperturbed [16] and study its stability under the influence of the temperature field and the pressure of the gas flow.…”

“…In this paper we consider the axisymmetric problem. In [16] the characteristics of the unperturbed state are determined, which have the following form:…”

“…Using the obtained characteristics of the unperturbed state, similarly to [16] we obtain the following nonlinear equation with respect to the displacement w(x, t) of the shell points…”

“…Substituting (17) into (16) we obtain the characteristic equation (with respect to β); its coefficients depend on the velocity parameter. The value of the parameter ν = ν cr at which two of the characteristic indicators become purely imaginary, and the rest still lie in the left half-plane, is critical, it corresponds to the critical velocity of the panel flutter in the linear formulation of this problem.…”

“…Similar problems were considered in detail in [10,11] taking into account the way the shell's edges were fixed. In the study of flutter in both linear and nonlinear formulations, a significant contribution was made by the representatives of the Armenian scientific school [12][13][14][15][16][17].…”