Pre- and Postflight Thermal Analysis of Test Launch Vehicle Fuselage

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Pre- and Postflight Thermal Analysis of Test Launch Vehicle Fuselage

Kim, Jongmin

This paper involves thermal analyses of the base and lateral wall of the test launch vehicle based on the flight result. The base is estimated to have $44 kW / m^{2}$ of heat flux and is covered by a thermal protection system to protect itself from the heat. The measured heat flux on the base is $44 - 55 kW / m^{2}$ in ground firing tests and $38 kW / m^{2}$ in the flight test. The temperature is maintained below $25 ° C$ during the flight. A significant convective heat flux, expected to arise from the recirculation, is observed in the subsonic region below 10 km of altitude when ascending. The heat flux and temperature of the lateral wall are estimated by considering the aerodynamic heating by external flow and the radiative cooling at the wall, and a thermal protection system is not applied. During most of the flight time, wall temperatures are maintained below $30 ° C$ . It is expected that the effect of solar radiation and heat loss on the cryogenic parts will appear to depend on the location.