Abstract
A high-speed aircraft, capable of maneuvering when moving in dense layers of the atmosphere, is subjected to high dynamic and thermal loads, which can lead to destruction of its shape and changes in its aerodynamic characteristics. Consequently, the main design objective is the thermal protection of structural elements of aircraft. Electron transpiration cooling is a prospective method for the solution of this problem. A mathematical model of the process of nonstationary heat exchange in the electron transpiration cooling system during convective heating has been formulated and studied. The effect of the evaporation (emission) of electrons from the emitter surface upon lowering the temperature of the composite shell of thermionic emission systems is shown. The influence of different coolants on the heat transfer in the thermionic converter was studied.
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