Volume 37 Issue 8
Sep 2022
Turn off MathJax
Article Contents
LI Junhong,LÜ Junming,MIAO Wenbo,et al.Real gas effects on the plasma sheath and the electromagnetic parameters of the reentry vehicle[J].Journal of Aerospace Power,2022,37(8):1579‑1586. doi: 10.13224/j.cnki.jasp.20210124
Citation: LI Junhong,LÜ Junming,MIAO Wenbo,et al.Real gas effects on the plasma sheath and the electromagnetic parameters of the reentry vehicle[J].Journal of Aerospace Power,2022,37(8):1579‑1586. doi: 10.13224/j.cnki.jasp.20210124

Real gas effects on the plasma sheath and the electromagnetic parameters of the reentry vehicle

doi: 10.13224/j.cnki.jasp.20210124
  • Received Date: 19 Mar 2021
    Available Online: 06 Sep 2022
  • Issue Publish Date: 28 Aug 2022
  • The numerical simulation technology of thermochemical non⁃equilibrium flow was established for aircraft hypersonic flight environment,the reliability of the calculation method was verified,and the influence law of high temperature real gas effect on plasma sheath and electromagnetic parameters in plasma was analyzed.The results showed:the numerical calculation results of aircraft peak plasma density on wall central line were in agreement with flight test results,as for the collision frequency,along the stagnation line,the two⁃temperature model and the Park reaction model had the same influence trend on the plasma collision frequency;for the relative dielectric constant,near the shock wave,the real part of other areas of the flow field was close to 1,and the imaginary part gradually increased along the stagnation line;The influence trend of the two⁃temperature model and the Park reaction model on the real and imaginary parts of the relative dielectric constant were consistent.

     

  • loading
  • [1]
    中国人民解放军总装备部军事训练教材编辑工作委员会.再入物理「M].北京:国防工业出版社,2005.
    [2]
    YAOBoA stochastic channel model of plasma sheath for hypersonic vehicle in near spaceXi'anXidian University2019(in Chinese)

    YAO Bo.A stochastic channel model of plasma sheath for hypersonic vehicle in near space[D].Xi'an:Xidian University,2019.(in Chinese)

    [3]
    CURTISJ TTRAMELR WThe AEDC thermochemical non⁃equilibrium package⁃theory and useAEDC⁃TR⁃93⁃201994

    CURTIS J T,TRAMEL R W.The AEDC thermochemical non⁃equilibrium package⁃theory and use[R].AEDC⁃TR⁃93⁃20,1994.

    [4]
    AKEYN DCROSSA ERadio blackout alleviation and plasma diagnostic results from a 25,000 foot per second blunt⁃body reentry⁃56151970

    AKEY N D,CROSS A E.Radio blackout alleviation and plasma diagnostic results from a 25,000 foot per second blunt⁃body reentry[R].NASA TN D⁃5615,1970.

    [5]
    GRANTHAMW LFlight results of a 25,000 foot per second re⁃entry experiment using microwave reflectometers to measure plasma electron density and standoff distance⁃60621970

    GRANTHAM W L.Flight results of a 25,000 foot per second re⁃entry experiment using microwave reflectometers to measure plasma electron density and standoff distance[R].NASA TND⁃6062,1970.

    [6]
    WEAVERW LBOWENJ TtrajectoryEntryentryenvironmentand analysis of spacecraft motion for the RAM C⁃Ⅲ flight experiment⁃25621972

    WEAVER W L,BOWEN J T.trajectory Entry,entry,environment,and analysis of spacecraft motion for the RAM C⁃Ⅲ flight experiment[R].NASA TM X⁃2562,1972.

    [7]
    JONESW LCROSSA EElectrostatic⁃probe measurements of plasma parameters for two reentry flight experiments at 25000 feet per second⁃66171972

    JONES W L,CROSS A E.Electrostatic⁃probe measurements of plasma parameters for two reentry flight experiments at 25000 feet per second[R].NASA TN D⁃6617,1972.

    [8]
    WEAVERW LMultiple⁃orifice liquid injection into hypersonic air streams and application to RAM C⁃Ⅲ flight⁃24861972

    WEAVER W L.Multiple⁃orifice liquid injection into hypersonic air streams and application to RAM C⁃Ⅲ flight[R].NASA TM X⁃2486,1972.

    [9]
    ZENGXiaofengModeling and scattering analysis of reentry and plasma sheathChengduUniversity of Electronic Science and Technology of China2018(in Chinese)

    ZENG Xiaofeng.Modeling and scattering analysis of reentry and plasma sheath[D].Chengdu:University of Electronic Science and Technology of China,2018.(in Chinese)

    [10]
    MENGGuipingRe‑entry body electromagnetic scattering characteristics analysis and algorithm researchNanjingNanjing University2019(in Chinese)

    MENG Guiping.Re‑entry body electromagnetic scattering characteristics analysis and algorithm research[D].Nanjing:Nanjing University,2019.(in Chinese)

    [11]
    WANGYanweiNumerical study on electron density and collision of sheath of hypersonic vehicleHarbinHarbin Institute of Technology2019(in Chinese)

    WANG Yanwei.Numerical study on electron density and collision of sheath of hypersonic vehicle[D].Harbin:Harbin Institute of Technology,2019.(in Chinese)

    [12]
    欧阳水吾.高温非平衡空气绕流[M].北京:国防工业出版社,2001.
    [13]
    GNOFFOP AGUPTAR NSHINNJ LConservation equations and physical models for hypersonic air flows in thermal and chemical non⁃equilibriumNASA TP⁃28671989

    GNOFFO P A,GUPTA R N,SHINN J L.Conservation equations and physical models for hypersonic air flows in thermal and chemical non⁃equilibrium[R].NASA TP⁃2867,1989.

    [14]
    ZHOUJingyunNumerical simulation of thermochemical non‑equilibrium hypersonic plasma flowBeijingChina Academy of Aerospace Aerodynamics2020(in Chinese)

    ZHOU Jingyun.Numerical simulation of thermochemical non‑equilibrium hypersonic plasma flow[D].Beijing:China Academy of Aerospace Aerodynamics,2020.(in Chinese)

    [15]
    PARKCAssessment of two temperature kinetic model for ionizing airAIAA⁃87⁃15741987

    PARK C.Assessment of two temperature kinetic model for ionizing air[R].AIAA⁃87⁃1574,1987.

    [16]
    MIAO W B,CHENU X L,AI B C.Flow configuration effects on mass diffusion part of heat flux in thermal⁃chemical flows[J].Acta Aerodynamica Sinica,2011,29(4):476⁃480.
    [17]
    苗文博,罗晓光,程晓丽,等.壁面催化对高超声速飞行器气动热性影响[J].空气动力学学报,2015,32(2):235⁃239.

    MIAO Wenbo,LUO Xiaoguang,CHENG Xiaoli,et al.Surface recombination effects on aerodynamic loads of hypersonic vehicles[J].Acta Aerodynamica Sinica,2015,32(2):235⁃239.(in Chinese)
    [18]
    LIOUM SA further development of the AUSM+ scheme towards robust and accurate solutions for all speeds⁃41162003

    LIOU M S.A further development of the AUSM+ scheme towards robust and accurate solutions for all speeds[R].AIAA 2003⁃4116,2003.

    [19]
    程晓丽,艾邦成,王强.基于分子平均自由程的热流计算壁面网格准则[J].力学学报,2010,42(6):1083⁃1089.

    CHENG Xiaoli,AI Bangcheng,WANG Qiang.A wall grid scale criterion based on the molecule mean free path for the wall heat flux computations by the Navier⁃Stokes equations[J].Chinese Journal of Theoretical and Applied Mechanics,2010,42(6):1083⁃1089.(in Chinese)
  • 加载中

Catalog

    Figures(20)

    Article Metrics

    Article views(43) PDF downloads(0) Cited by()
    Proportional views
    Related

    /

    DownLoad:  Full-Size Img  PowerPoint
    Return
    Return