| 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
|
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.
| [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] |
姚博.高速飞行器等离子鞘套信道统计模型研究[D].西安:西安电子科技大学,2019.
YAO Bo.A stochastic channel model of plasma sheath for hypersonic vehicle in near space[D].Xi'an:Xidian University,2019.（in Chinese）
|
| [3] |
CURTIS J T,TRAMEL R W.The AEDC thermochemical non⁃equilibrium package⁃theory and use[R].AEDC⁃TR⁃93⁃20,1994.
|
| [4] |
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] |
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] |
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] |
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] |
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] |
曾啸风.再入飞行物及等离子体鞘套的建模与散射分析[D].成都:电子科技大学,2018.
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] |
孟贵平.再入体的电磁散射特性分析及算法研究[D].南京:南京大学,2019.
MENG Guiping.Re‑entry body electromagnetic scattering characteristics analysis and algorithm research[D].Nanjing:Nanjing University,2019.（in Chinese）
|
| [11] |
王艳薇.高超飞行器鞘套电子密度与碰撞的数值研究[D].哈尔滨:哈尔滨工业大学,2019.
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] |
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] |
周靖云.高超声速热化学非平衡等离子体流场数值模拟[D].北京:中国航天空气动力技术研究院,2020.
ZHOU Jingyun.Numerical simulation of thermochemical non‑equilibrium hypersonic plasma flow[D].Beijing:China Academy of Aerospace Aerodynamics,2020.（in Chinese）
|
| [15] |
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] |
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）
|
DownLoad:
