火星探测是目前国际深空探测的热点，而火星着陆是火星探测的关键技术之一，火星着陆器发展中面临的一个严峻的挑战是其气动环境远远不同于地球大气的空气。然而，现阶段大多数地面试验设备都是以空气为试验气体来设计的，而不是火星大气的CO2。本文利用高温热化学反应流动数值计算技术，对JF-12反向爆轰驱动激波风洞在火星进入环境下（主要气体成分是CO2）的运行特性进行了计算模拟，通过调整激波管中驱动/被驱动气体的初始参数和高/低压段的截面积比，来模拟其中的波系产生、传播过程以及反射激波与接触面的相互作用机制。研究发现，相同情况下驱动CO2的缝合激波马赫数要明显高于空气，通过减小驱动气体的声速和低压段的直径，可以在驱动CO2时获得驻室压力稳定的试验气体。
Martian spacecraft landing is one of the key technologies for Mars exploration which is one of the hotspots of current international deep space exploration. A serious challenge in the development of Martian landing technology is that the aerodynamic environment on the Mars is far different from the atmosphere on the Earth. However, most of the ground-based aerodynamic test facilities are designed initially for flow tests of air, instead of the carbon dioxide in the Martian atmosphere. In this work, we use the numerical calculation technology of high temperature thermochemical reacting flow to simulate the operating characteristics of the new built hypersonic shock tunnel (JF-12) for hypersonic model tests in the atmosphere of Mars (mainly carbon dioxide). By adjusting the driver/driven gas parameters and the cross section area of the driven section, the interaction mode between reflected shock waves and contact surfaces can be trimmed for the tailored-interface operation condition in the simulation. It is found that the tailored shock Mach number of the driving carbon dioxide is significantly larger than that of the driving air, when only the type of the test gas is changed. Steady stagnation pressure can be achieved in the test gas of carbon dioxide by reducing the driven-to-driver cross area ratio and replacing the diluting gas N2 with CO2 in the detonation driver.
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