Transactions of Nanjing University of Aeronautics & Astronautics
Thermoelastic Stability of Closed Cylindrical Shell in Supersonic Gas Flow
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Abstract:
In a linear framework, the problem of stability of closed cylindrical shell is briefly discussed. The cylindrical shell is immersed in a supersonic gas flow and under the influence of temperature field varying along the thickness. An unperturbed uniform velocity flow field, directed along the short edges of the shell, is applied. Due to the inhomogeneity of the temperature field distribution across the thickness shell buckling instability occurs. This instability accounts for the deformed shape of the shell, to be referred as the unperturbed state. Stability conditions and boundary for the unperturbed state of the system under consideration are presented following the basic theory of aero-thermo-elasticity. The stability boundary depends on the variables characterizing the flow speed, the temperature at the middle plane of the shell and the temperature gradient in the direction normal to that plane. It is shown that the combined effect of the temperature field and flowing stream regulates the process of stability, and the temperature field can significantly change the flutter critical speed.
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The authors would like to express thanks to the European funded FP7 Marie Curie Action A2-Net-Team Project dedicated to the investigation of aeroelastic behaviour of innovative unmanned aircraft such as HALE UAV. The work was supported by State Committee Science MES RA, in frame of the research project No. SCS 13-2C243.
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