Post-Flight TPS Analysis of Hayabusa Reentry Capsule

The thermal response of ablative TPS of the Hayabusa capsule is calculated along the most probable reentry trajectory by using the integrated analysis method. The analysis method consists of an axisymmetric nonequilibrium Navier-Stokes flow solver and the radiative heat transfer analysis code loosely coupled to a ablation thermal response code. The calculated results are compared with the flight data obtained at the present time. It is found that a reasonable agreement is obtained between the calculated surface temperature and the temperature values estimated from blackbody spectrum obtained by DC-8 airborne observation and the ground observation. The calculated surface recession overestimates the measurement along the wall surface by a factor of three. On the contrary, the density distributions calculated by taking account of nitration reaction reproduce the flight data moderately both at the stagnation point and the downstream region. Especially in the downstream region, the calculated thickness of char lyer overestimates the flight data when we consider the effect of turbulence due to the pyrolysis gas, while it underestimates the flight data when the effect of surface roughness of ablative TPS is taken into account.

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