High-Energy Atmospheric Reentry Test Aerothermodynamic Analysis

The aerothermodynamic environment around an 8.3 m High-Energy Atmospheric Reentry Test vehicle is assessed. Twelve nose-shape configurations are generated, and their responses at the peak heating trajectory point are compared against the baseline nose shape. The possibility of a two-piece thermal protection system design at the nose is also considered, as are the surface catalytic affects of the aeroheating environment of such a configuration. Based on these analyses, an optimum nose shape is proposed to minimize the surface heating. The heat flux sensitivity of the optimum geometry to the angle of attack variations are also studied. A recommendation is also made for a two-piece thermal protection system design, for which the surface catalytic uncertainty associated with the jump in heating at the nose-inflatable aerodynamic decelerator juncture is reduced by a minimum of 93%. In this paper, the aeroshell is assumed to be rigid, and the inflatable fluid interaction effect is left for future investigations.