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Numerical Investigation of Plasma Active Flow Control 被引量：1

Numerical Investigation of Plasma Active Flow Control
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摘要 Based on the theory of EHD （electronhydrodynamic）, a simplified volume force model is applied to simulation to analyze the traits of plasma flow control in flow field, in which the cold plasma is generated by a DBD （dielectric-barrier-discharge） actuator. With the para- electric action of volume force in electric field, acceleration characteristics of the plasma flow are investigated for different excitation intensities of RF （radio frequency） power for the actuator. Furthermore, the plasma acceleration leads to an asymmetric distribution of flow field, and hence induces the deflection of jet plume, then results in a significant deflection angle of 6.26° thrustvectoring effect. It appears that the plasma flow control technology is a new tentative method for the thrust-vectoring control of a space vehicle. Based on the theory of EHD （electronhydrodynamic）, a simplified volume force model is applied to simulation to analyze the traits of plasma flow control in flow field, in which the cold plasma is generated by a DBD （dielectric-barrier-discharge） actuator. With the para- electric action of volume force in electric field, acceleration characteristics of the plasma flow are investigated for different excitation intensities of RF （radio frequency） power for the actuator. Furthermore, the plasma acceleration leads to an asymmetric distribution of flow field, and hence induces the deflection of jet plume, then results in a significant deflection angle of 6.26° thrustvectoring effect. It appears that the plasma flow control technology is a new tentative method for the thrust-vectoring control of a space vehicle.
作者 孙佰刚 李锋 张珊珊 王靖宇 张莉涓 赵二雷
机构地区 School of Jet Propulsion Beijing University of Aeronautics and Astronautics Aviation University of Air Force
出处 《Plasma Science and Technology》 SCIE EI CAS CSCD 2010年第6期723-728,共6页 等离子体科学和技术（英文版）
基金 supported by National Natural Science Foundation of China (No.90716025)
关键词 flow control PLASMA thrust-vectoring DBD EHD flow control, plasma, thrust-vectoring, DBD, EHD
分类号 O53 [理学—等离子体物理]
  • 相关文献

参考文献15

  • 1Shneider Mikhail N, Macheret Sergey O. 2005, Hypersonic Aerodynamic Control and Thrust Vectoring by Nonequilibrium Cold-Air MHD Devices. Presented at 43rd Aerospace Sciences Meeting and Exhibit, Reno, USA, American Institute of Aeronautics and Astronautics.
  • 2Blankson Isaiah M, Schneider Stephen. 2003, Hypersonic Engine using MHD Energy Bypass with a Conventional Turbojet. Presented at the 12th AIAA International Space Planes and Hypersonic Systems and Technologies, Norfolk, USA, American Institute of Aeronautics and Astronautics.
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  • 4Kumar Haribalan, Roy subrata. 2005, Hydrodynamic Model of Plasma-Sheath for RF Discharges with and without Collision. Presented at the 43rd AIAA Aerospace Sciences Meeting and Exhibit, Reno, USA, American Institute of Aeronautics and Astronautics.
  • 5Reece Roth J, Hojung Sin, Taja Chandra Mohan Madhan, et al. 2003, Flow Re-attachment and Acceleration by paraelectric and Peristaltic Electronhydrodynamic (EHD) Effects. presented at the 41st Aerospace Sciences Meeting and Exhibit Reno, USA, American Institute of Aeronautics and Astronautics.
  • 6Reece Roth J, Xin Dai. 2006, Optimization of the Aerodynamic Plasma Actuator as an Electrohydrodynamic(EHD) Electrical Device. Presented at the 44th Aerospace Sciences Meeting and Exhibit, Reno, USA, American Institute of Aeronautics and Astronautics.
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同被引文献12

  • 1Sergey O M,lkhail N S, Richard B M, et al. Magnetohydrody- namic and electrohydrodynamic control of hypersonic flows of weakly ionized plasmas, A1AA-2004-0427 [ R ]. Reston: AIAA, 2004.
  • 2Peter P,Rodney M, Elke P,et al. MHD effect on a supersonic. weakly ionized flow [ C ]//33rd Plasmadynamies and Lasers Con- ferenee. Reston : A IAA, 2002 : 2002-2246.
  • 3Murray R C,Vasilyak L,Carraro M R,et al. Observation of MHD effects with nonequilibrium ionization in coht supersonic air flows, AIAA-2004-1025 [ R ]. Reston :AIAA, 2004.
  • 4Kuranov A L,Sheikin E G. MHD control on hypersonic aircraft under AJAX concept: Possibilities of M HI) generator[ C ]//A IAA Aerospace Sciences Meeting and Exhibit. Reston : AIAA, 2002 : 14-17.
  • 5Vatazhin A, Kopchenov V, Gouskov O. Some estimations of pos- sibility to use the MHD control for hypersonic flow deceleration, AIAA-1999-4972 [ R ]. Reston : AIAA, 1999.
  • 6Lineberry J T, Begg L L, Castro J H, et al. Scramjet driven MHD power demonstration: HVEPS project overview ,AIAA-2006-8010 [ R ]. Reston : AIAA ,2006.
  • 7Corke T C ,Jumper E J. Application of weakly-lonized plasmas as wing flow-control, A1AA-2002-0305 [ R ]. Reston : AIAA, 2002.
  • 8Mikhail N S, Sergey 0 M. Hypersonic aerodynamic control and thrust vectoring by nonequilibrium cold-air MHD devices [ J]. Journal of Propulsion and Power,2006,22 ( 3 ) :490-497.
  • 9Macheret S O, Shneider M N, Miles R B. Magnetohydrodynamic control of hypersonic flows and scramjet inlets using electron beam ionization [ J ]. AIAA Paper, 2002 ( 40 ) :74-81.
  • 10Sun B G, Li F, Yang H. Experiment investigation of plasma plume deflection with MHD[ C ] JJ Proceedings of International Conference on Electronics and Optoelectronics. Piscataway, N J:IEEE Press,2011,1:142-145.

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Plasma Science and Technology
2010年 第6期

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