Abstract
The purpose of the present study is to develop a shock tube facility for nonequilibrium radiation studies in Mars entry flight conditions. For the purpose, characteristic investigations and radiation measurements are conducted using the newly developed shock tube facility. In the characteristic investigations, compression process is analyzed by compression tests and numerical analysis to decide the optimum operating condition. Shock velocity at the test section is measured and compared with actual flight data to examine the performance of the facility. In radiation measurements, shock front radiation is measured using the newly developed multipoint spectroscopic measurement system. As a result, the optimum operating condition to achieve soft landing operation is obtained. From the shock velocity measurements, it is found that the shock tube can simulate typical Mars entry flight conditions. The multipoint spectroscopic measurement system enables us to observe a spatial profile of emission spectrum with high accuracy. In conclusion, the newly developed shock tube facility can be used for nonequilibrium radiation studies in Mars entry flight conditions.
