Improvement of prediction accuracy for thermochemical nonequilibrium processes around vehicles entering in carbon dioxide atmosphere

为了研究激波后的热化学非平衡现象，研制了一种模拟火星进入飞行条件的高超声速激波管。新开发的多点光谱测量系统使我们能够获得冲击波后面的辐射光谱的空间分布。温度的空间分布可以通过应用CAMS（计算机辅助分子光谱学）方法使用辐射分析代码来获得。

Hypersonic shock tube simulating Mars entry flight conditions was newly developed to investigate the thermochemical nonequilibrium phenomena behind a shock wave. The newly developed multipoint spectroscopic measurement system enables us to obtain the spatial profile of radiation spectra behind a shock wave. The spatial profile of temperatures can be obtained by applying the CAMS (Computer aided molecular spectroscopy) method using the radiation analysis code.