航空学报 > 2021, Vol. 42 Issue (3): 124129-124129   doi: 10.7527/S1000-6893.2020.24129

JF-12激波风洞在火星进入环境下的运行特性

韩子健1,2, 彭俊1,2, 胡宗民1,2, 韩桂来1, 姜宗林1,2   

  1. 1. 中国科学院 力学研究所 高温气体动力学国家重点实验室, 北京 100190;
    2. 中国科学院大学 工程科学学院, 北京 100049
  • 收稿日期:2020-04-23 修回日期:2020-05-05 发布日期:2020-05-21
  • 通讯作者: 胡宗民 E-mail:huzm@imech.ac.cn
  • 基金资助:
    国家自然科学基金(11672308,11532014);国家重点研发计划(2019YFA0405204)

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

HAN Zijian1,2, PENG Jun1,2, HU Zongmin1,2, HAN Guilai1, JIANG Zonglin1,2   

  1. 1. State Key Laboratory of High-temperature Gas Dynamics(LHD), Institute of Mechanics, Chinese Academy of Sciences, Beijing 100190, China;
    2. School of Engineering Science, University of Chinese Academy of Sciences, Beijing 100049, China
  • Received:2020-04-23 Revised:2020-05-05 Published:2020-05-21
  • Supported by:
    National Natural Science Foundation of China (11672308, 11532014);National Key R&D Program of China(2019YFA0405204)

摘要: 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。

关键词: 火星探测, 反向爆轰驱动激波风洞, 二氧化碳, 缝合运行状态, 驻室压力

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

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