Abstract
The aim is to present a method of coupling aerodynamic convective heating, radiative exchange, and thermal conduction. The models that describe heat conduction within thermal-protection-system (TPS) materials and radiative exchange at the surface of space vehicles have been developed to supplement catalysis modeling at the surface with the aim of accurate prediction of the thermal loads during reentry. These models have been developed for the three-dimensional parallel-multiblock (P-MB) URANUS (upwind relaxation algorithm for nonequilibrium flows of the University of Stuttgart) code. The influence of radiative exchange and thermal conduction within the TPS material on the catalysis and the gas state at the surface, and thus on the heat load distribution at the surface, is demonstrated for the reentry vehicles COLIBRI and X-38 with real TPS coating.
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