<p>The paper discusses computational and experimental methods for determining the thermo-erosion characteristics of launch escape propulsion subsystems (LEPS) thermal protection coatings under natural operating conditions. Combustion mixture flow was simulated using a commercial CFD software. Based on the obtained data, heat flux distribution across the LEPS surface was determined. Firing tests conditions of thermal protection materials are also described. A gas-dynamic tunnel (GDT) was used to reproduce the natural operating conditions. Quantitative characteristics of thermo-erosion resistance for materials were calculated based on the experimental results with corrections for the period of transient coating heating.</p>