磁激等离子体超声速气流的瞬态加速系统及其实验研究

流体力学与飞行力学

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磁激等离子体超声速气流的瞬态加速系统及其实验研究

朱涛, 李应红, 张百灵, 陈峰, 李益文

空军工程大学等离子体动力学重点实验室, 陕西西安 710038

收稿日期:2011-10-11 修回日期:2011-11-30 出版日期:2012-08-25 发布日期:2012-08-23
通讯作者: 李应红 E-mail:yinghong_li@126.com
基金资助:
国家自然科学基金(10972236)

Transient Acceleration System of Magnetoplasmadynamic Supersonic Airstream and Its Experimental Research

ZHU Tao, LI Yinghong, ZHANG Bailing, CHEN Feng, LI Yiwen

Science and Technology on Plasma Dynamics Laboratory, Air Force Engineering University, Xi’an 710038, China

Received:2011-10-11 Revised:2011-11-30 Online:2012-08-25 Published:2012-08-23
Supported by:
National Natural Science Foundation of China (10972236)

摘要/Abstract

摘要： 研制了基于激波风洞的热电离系统,设计了马赫数Ma=1.5的喷管和分段法拉第型实验段,并选用了合理的磁场及电场方案。采用氦气驱动氩气模式,通过在激波管低压段注入电离种子K₂CO₃粉末实现气流的热电离;压缩后的高温氩气启动喷管,以瞬态超声速导电流体形式通过实验段。实验结果表明:当激波管高压段压力为1.1 MPa、低压段压力为500 Pa时,喷管出口的超声速导电气流温度约为4 185.91 K,压力约为0.037 MPa;当电容电压为400 V、磁感应强度为1.0 T时,由实验段中间位置电极的放电特性可以估算出气流电导率约为78.1 S/m,单对电极输入功率约为9.46 kW;用感应电压法对加速效果进行初步评估,出口气流速度增加了29.3%,电效率为26.1%。

关键词: 等离子体, 超声速, MPD/MHD加速, 热电离, 激波风洞, 电导率

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

中图分类号:

朱涛, 李应红, 张百灵, 陈峰, 李益文. 磁激等离子体超声速气流的瞬态加速系统及其实验研究[J]. 航空学报, 2012, 33(8): 1375-1383.

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.

参考文献

[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.

E-mail：hkxb@buaa.edu.cn

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磁激等离子体超声速气流的瞬态加速系统及其实验研究

Transient Acceleration System of Magnetoplasmadynamic Supersonic Airstream and Its Experimental Research

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