Establishment of prediction technique for flight environment for high-speed reentry vehicle

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In a sample return mission for the planetary exploration, the technology for the high-speed reentry is required. For the development of a vehicle with such a high-speed reentry, the knowledge for the aerodynamic heating environment is important. For this purpose, the experimental data is especially important. Nevertheless, obtaining the data on the elementally process for the high-enthalpy flow is quite difficult. Therefore, the physical property in the shock layer was carefully measured by means of the shock tube of free-piston type. Based on the measured distribution of the physical properties, the thermochemical model for the high-enthalpy flow was constructed. First, the nitrogen gas was investigated for simplicity. We found not only various thermal non-equilibrium, but also the significant increase of the electron number density, which were not recognized previously. Based on these measurements, the new thermochemical model was constructed. Next, the air was investigated. Even in the air, we found the similar feature in the chemical species originated from Nitrogen. In addition to the chemical species originated from Nitrogen, the chemical species originated from Oxygen was investigated by means of the absorption spectroscopic measurement. Based on these measurements, the thermo-chemical model was newly proposed, which can explain the distribution of the physical properties in the shock layer generated by the high-speed shock wave. These results can be very usefull for the development of a vehicle with high-speed reentry.