Simulating the flight operating conditions of a launch escape propulsion subsystem with a thermal protection coating
R.D. Berdov1, L.I. Volkova1, A.S. Golovatyuk1, D.L. Potemkin2, V.K. Batygina2
1АJSC “Keldysh Research Center”, Moscow, Russia
2JSC ”Corporation “MITT”, Moscow, Russia
Keywords: launch escape propulsion subsystem, thermal protection coating, high-altitude operating conditions simulation, experimental modeling
Abstract
The paper discusses computational and experimental methods for evaluation the thermo-erosion characteristics of launch escape propulsion subsystems (LEPS) equipped with a thermal protection coating 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 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 non-stationary coating heating.
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