Abstract

For the thermal protection of a reusable space system, from the moment of prelaunch preparation to the completion of the flight program-landing, there are about twenty external factors. These include intensive aerodynamic heating with the different chemical composition of the atmosphere, high and low temperatures, sudden changes in atmospheric pressure, mechanical stresses caused by gas dynamics of supersonic flows, momentum, and shock. Reliable operation of thermal protection is the key to the successful operation of the reusable space system, therefore, experimental and theoretical studies of thermal protection under high-temperature influences are of particular relevance. Here is offered the technique of bench high-temperature tests of heat-protective materials of repeated use. The tests were carried out on a supersonic gas dynamic bench under the influence of high-intensity energy flows As a result of the experiment, a temperature field was obtained at the surface and in the depth of the heat-shielding material at different points of time. A mathematical model adequately describing the distribution of the temperature field in heat-shielding materials is developed under the action of high-intensity energy fluxes on them. The obtained theoretical results are compared with the experimental data.

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