磁激等离子体超声速气流的瞬态加速系统及其实验研究

Abstract

Abstract: A hot ionization experimental system based on a shock tunnel is developed. A supersonic nozzle (Mach number Ma=1.5) and a test section (segmented Faraday accelerator) are scientifically designed as well as a magnetic & electric field scheme. Helium is chosen as the driver gas while argon as the driven gas, and ionization of the airstream is realized by adding K₂CO₃ powder into the driven section. The compressed argon with a high temperature drives the nozzle and creates a transient supersonic electric airstream in the test section. The experimental results are as follows: the temperature and pressure of the airstream is 4 185.91 K and 0.037 MPa respectively under the condition of 1.1 MPa driver pressure and 500 Pa driven pressure; when voltage of capacitor is 400 V and magnetic induction is 1.0 T, the electric conductivity is estimated to be 78.1 S/m with a 9.46 kW input power obtained by analyzing the discharge data of a single electrode pair; the speed of the outlet airstream is evaluated to register an increase of 29.3% and the electric efficiency is shown to be approximately 26.1% as calculated by the induced voltage.

Key words: plasma, supersonic speed, MPD/MHD acceleration, hot ionization, shock tunnel, electric conductivity

CLC Number:

ZHU Tao, LI Yinghong, ZHANG Bailing, CHEN Feng, LI Yiwen. Transient Acceleration System of Magnetoplasmadynamic Supersonic Airstream and Its Experimental Research[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2012, 33(8): 1375-1383.

References

[1] Mao G W, Tang J L. Propulsion system of space vehicle and its application. Xi’an: Press of Northwestern Polytechnical University, 2009: 7. (in Chinese) 毛根旺, 唐金兰. 航天器推进系统及其应用. 西安: 西北工业大学出版社, 2009: 7.
[2] Zheng X M, Lu H Y, Xu D J, et al. Optimization of accelerator mode MHD controlled inlet. Acta Aeronautica et Astronautica Sinica, 2010, 31(2): 223-230. (in Chinese) 郑小梅, 吕浩宇, 徐大军, 等. MHD加速器模式磁控进气道的优化设计. 航空学报, 2010, 31(2): 223-230.
[3] Sheikin E G, Kuranov A L. Scramjet with MHD bypass under "AJAX" concept. AIAA-2004-1192, 2004.
[4] Lu H Y, Conceptual study on integrated design of airframe/MHD bypass scramjet for a waverider-based hypersonic vehicle. Beijing: School of Aeronautic Science and Engineering, Beihang University, 2008.(in Chinese) 吕浩宇. 高超声速乘波构型飞行器磁流体进气道一体化研究. 北京: 北京航空航天大学航空科学与工程学院, 2008.
[5] Zheng X M. Numerical investigation of the MHD technology in hypersonic vehicle application. Beijing: School of Astronautics, Beihang University, 2009. (in Chinese) 郑小梅. 高超声速飞行器磁流体技术数值模拟研究. 北京: 北京航空航天大学宇航学院, 2009.
[6] Yu D R, Tang J F, Bao W. MHD-arc-ramjet combined cycle for hypersonic propulsion. Acta Aeronautica et Astronautica Sinica, 2007, 28(4): 769-775. (in Chinese) 于达仁, 唐井峰, 鲍文. 用于高超声速推进的MHD-arc-ramjet联合循环. 航空学报, 2007, 28(4): 769-775.
[7] Zhang K P, Tian Z Y, Feng D H, et al. Numerical study of acceleration/deceleration control of three-dimensional magnetohydrodynamic flow in channel. Acta Aerodynamica Sinica, 2009, 27(4): 474-479. (in Chinese) 张康平, 田正雨, 冯定华, 等. 三维磁流体动力学管道流动加减速控制数值研究. 空气动力学报, 2009, 27(4): 474-479.
[8] Su C B, Li Y H, Cheng B Q, et al. Experimental investigation of MHD flow control for the oblique shock wave around the ramp in low-temperature supersonic flow. Chinese Journal of Aeronautics, 2010, 22(1): 22-32.
[9] Wang J, Li Y H, Cheng B Q, et al. Experimental investigation on shock wave control by plasma aerodynamic actuation. Acta Aeronautica et Astronautica Sinica, 2009, 30(8): 1374-1379. (in Chinese) 王健, 李应红, 程邦勤, 等. 等离子体气动激励控制激波的实验研究. 航空学报, 2009, 30(8): 1374-1379.
[10] Wang J, Li Y H, Cheng B Q, et al. Mechanism investigation on shock wave control by plasma aerodynamic actuation. Acta Physica Sinica, 2009, 58(8): 5513-5519. (in Chinese) 王健, 李应红, 程邦勤, 等. 等离子体气动激励控制激波的机理研究. 物理学报, 2009, 58(8): 5513-5519.
[11] Wang J, Li Y H, Cheng B Q, et al. Investigation on oblique shock wave control by arc discharge plasma in supersonic airflow. Journal of Applied Physics, 2009, 106(7): 73307-73314.
[12] Wang J, Li Y H, Cheng B Q, et al. Effects of plasma aerodynamic actuation on oblique shock wave in a cold supersonic flow. Journal of Physics D: Applied Physics, 2009, 42(16): 165503-165511.
[13] Li Y W, Li Y H, Zhang B L, et al. Supersonic magnetohydyodynamic technical experimental system dased on shock tunnel. Acta Aeronautica et Astronautica Sinca, 2011, 32(6): 1015-1024. (in Chinese) 李益文, 李应红, 张百灵, 等. 基于激波风洞的超声速磁流体动力技术实验系统. 航空学报, 2011, 32(6): 1015-1024.
[14] Su W Y, Zhang X Y, Zhang K Y. Numerical investigation of Lorentz force control on hypersonic inlet boundary layer separation. Journal of Propulsion Technology, 2011, 32(1): 36-41. (in Chinese) 苏纬仪, 张新宇, 张堃元. 洛伦兹力控制高超声速进气道边界层分离的数值模拟. 推进技术, 2011, 32(1): 36-41.
[15] Macheret S O. Physics of magnetically accelerated non-equilibrium surface discharge in high-speed flow. AIAA-2006-1005, 2006.
[16] Kalra C, Zaidi S H, Alderman B J, et al. Non-thermal control of shock-wave induced boundary layer separation using magneto-hydro-dynamics. AIAA-2007-4138, 2007.
[17] Bogdanoff D W, Mehta U B. Experimental demonstration of magneto-hydro-dynamics (MHD) acceleration. AIAA-2003-4285, 2003.

Transient Acceleration System of Magnetoplasmadynamic Supersonic Airstream and Its Experimental Research

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