JF-12激波风洞在火星进入环境下的运行特性

doi:10.7527/S1000-6893.2020.24129

Abstract

Abstract: 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.

Key words: Mars exploration, backward detonation-driven shock tunnels, carbon dioxide, tailored interface conditions, stagnation pressure

CLC Number:

V216.8

HAN Zijian, PENG Jun, HU Zongmin, HAN Guilai, JIANG Zonglin. Operating characteristics of JF-12 shock tunnel in Mars entry tests[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2021, 42(3): 124129-124129.

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Operating characteristics of JF-12 shock tunnel in Mars entry tests

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