李斌 , 刘琪 , 徐琰珂 . 美国未来空空导弹发展与能力 [J ] . 航空兵器 , 2023 , 30 ( 2 ): 83 - 90 .

LI B , LIU Q , XU Y K . Development and capability of American air-to-air missile in the future [J ] . Aero Weaponry , 2023 , 30 ( 2 ): 83 - 90 . (in Chinese)

李玮 , 程磊 , 逯怀刚 , 等 . 俄乌冲突中反辐射导弹的作战运用与启示 [J ] . 航天电子对抗 , 2023 , 39 ( 3 ): 5 - 9 .

LI W , CHENG L , LU H G , et al . Combat use and enlightenment for anti-radiation missile in the Russia-Ukraine conflict [J ] . Aerospace Electronic Warfare , 2023 , 39 ( 3 ): 5 - 9 . (in Chinese)

刘东矗 , 刘新雄 . 美军高超声速导弹作战运用的关键问题分析 [J ] . 战术导弹技术 , 2023 ( 3 ): 142 - 148 .

LIU D C , LIU X X . Analysis on key operational problems of the US military hypersonic missiles [J ] . Tactical Missile Technology , 2023 ( 3 ): 142 - 148 . (in Chinese)

王毓龙 , 刘曰胜 , 赵玲 , 等 . 以色列国家导弹防御体系建设发展研究 [J ] . 中国电子科学研究院学报 , 2023 , 18 ( 1 ): 97 - 102 .

WANG Y L , LIU Y S , ZHAO L , et al . Research on the construction and development of Israel national missile defense system [J ] . Journal of China Academy of Electronics and Information Technology , 2023 , 18 ( 1 ): 97 - 102 . (in Chinese)

刘颖 , 任春艳 . 2021年国外空地导弹发展动态研究 [J ] . 航空兵器 , 2022 , 29 ( 5 ): 11 - 20 .

LIU Y , REN C Y . Research on foreign air-to-ground missiles development in 2021 [J ] . Aero Weaponry , 2022 , 29 ( 5 ): 11 - 20 . (in Chinese)

任淼 , 刘晶晶 , 文琳 . 2021年国外空空导弹发展动态研究 [J ] . 航空兵器 , 2022 , 29 ( 4 ): 33 - 41 .

REN M , LIU J J , WEN L . Research on foreign air-to-air missiles development in 2021 [J ] . Aero Weaponry , 2022 , 29 ( 4 ): 33 - 41 . (in Chinese)

赵彪 . 高超声速飞行器技术发展研究 [D ] . 哈尔滨 : 哈尔滨工业大学 , 2010 .

ZHAO B . Research on the development of hypersonic vehicle technology [D ] . Harbin : Harbin Institute of Technology , 2010 . (in Chinese)

STAFF W . US military loses contact with hypersonic air-craft [EB/OL ] . (2011-08-12)[2023-08-19 ] . https://www.bbc.com/news/world-us-canada-14497641. https://www.bbc.com/news/world-us-canada-14497641 https://www.bbc.com/news/world-us-canada-14497641

赵鹏飞 , 董长虹 . 高超声速飞行器关键技术发展分析 [J ] . 飞航导弹 , 2017 ( 10 ): 37 - 44 .

ZHAO P F , DONG C H . Development analysis of hypersonic vehicle key technologies [J ] . Aerodynamic Missile Journal , 2017 ( 10 ): 37 - 44 . (in Chinese)

周岩 , 罗振兵 , 王林 , 等 . 等离子体合成射流激励器及其流动控制技术研究进展 [J ] . 航空学报 , 2022 , 43 ( 3 ): 90 - 132 .

ZHOU Y , LUO Z B , WANG L , et al . Plasma synthetic jet actuator for flow control:review [J ] . Acta Aeronautica et Astronautica Sinica , 2022 , 43 ( 3 ): 90 - 132 . (in Chinese)

夏智勋 , 王林 , 周岩 , 等 . 等离子体高能合成射流 [M ] . 北京 : 科学出版社 , 2022 .

XIA Z X , WANG L , ZHOU Y , et al . Plasma high energy synthetic jet [M ] . Beijing : Science Press , 2022 . (in Chinese)

李应红 , 吴云 , 梁华 , 等 . 等离子体激励气动力学探索与展望 [J ] . 力学进展 , 2022 , 52 ( 1 ): 1 - 32 .

LI Y H , WU Y , LIANG H , et al . Exploration and outlook of plasma-actuated gas dynamics [J ] . Advances in Mechanics , 2022 , 52 ( 1 ): 1 - 32 . (in Chinese)

MESSIER D . AIAA names top 10 emerging aerospace te-chnologies [EB/OL ] . (2009-06-10)[2023-08-19 ] .https://parabolicarc.com/2009/06/10/aiaa-names-top-10-emerging-aeorspace-technologies/. https://parabolicarc.com/2009/06/10/aiaa-names-top-10-emerging-aeorspace-technologies/ https://parabolicarc.com/2009/06/10/aiaa-names-top-10-emerging-aeorspace-technologies/

王林 . 等离子体高能合成射流及其超声速流动控制机理研究 [D ] . 长沙 : 国防科学技术大学 , 2014 .

WANG L . Principle of plasma high-energy synthetic jet and supersonic flow control [D ] . Changsha : National University of Defense Technology , 2014 . (in Chinese)

MOREAU E . Airflow control by non-thermal plasma actuators [J ] . Journal of Physics D: Applied Physics , 2007 , 40 ( 3 ): 605 - 636 .

BELINGER A , HARDY P , GHERARDI N , et al . Influence of the spark discharge size on a plasma synthetic jet actuator [J ] . IEEE Transactions on Plasma Science , 2011 , 39 ( 11 ): 2334 - 2335 .

BELINGER A , HARDY P , BARRICAU P , et al . Influence of the energy dissipation rate in the discharge of a plasma synthetic jet actuator [J ] . Journal of Physics D: Applied Physics , 2011 , 44 ( 36 ): 365201 .

GROSSMAN K , CYBYK B , WIE D . Spark jet actuators for flow control [C ] // Proceedings of the 41st Aerospace Sciences Meeting and Exhibit. Reno, NV , US : AIAA , 2003 .

ADAMOVICH I , BAALRUD S D , BOGAERTS A , et al . The 2017 plasma roadmap: low temperature plasma science and technology [J ] . Journal of Physics D: Applied Physics , 2017 , 50 ( 32 ): 323001 .

张小兵 , 袁亚雄 , 谢玉树 . 等离子体点火密闭爆发器实验研究 [J ] . 火炸药学报 , 2003 , 26 ( 2 ): 24 - 26 , 31. 利用某反坦克火箭弹用改型双基管状推进剂装药生产定型的13个成品批次的物理性能、弹道性能、药型尺寸等验收测试数据进行综合分析，得出改型双基管状推进剂装药弹道性能指标参数通用计算公式及其相互关系。

ZHANG X B , YUAN Y X , XIE Y S . Experimental study on gun propellant plasma ignition in closed bomb [J ] . Chinese Journal of Explosives & Propellants , 2003 , 26 ( 2 ): 24 - 26 , 31. (in Chinese)

张小兵 , 袁亚雄 , 陈键 , 等 . 含能材料等离子体点火过程的数值模拟 [J ] . 南京理工大学学报(自然科学版) , 2004 , 28 ( 3 ): 295 - 298 .

ZHANG X B , YUAN Y X , CHEN J , et al . Numerical simulation of plasma ignition of energetic materials [J ] . Journal of Nanjing University of Science and Technology (Natural Science) , 2004 , 28 ( 3 ): 295 - 298 . (in Chinese)

ZONG H H , KOTSONIS M . Formation, evolution and scaling of plasma synthetic jets [J ] . Journal of Fluid Mechanics , 2018 , 837 : 147 - 181 .

ZHANG B , ZHANG X B . Modeling of plasma density, argon ion energy and ion velocity functions in a dipolar electron cyclotron resonance plasma source [J ] . Vacuum , 2020 , 174 : 109215 .

袁亚雄 , 张小兵 . 高温高压多相流体动力学理论与应用 [M ] . 北京 : 北京理工大学出版社 , 2016 .

YUAN Y X , ZHANG X B . Theories and applications of multiphase fluid dynamics in high temperature and high pressure [M ] . Beijing : Beijing Institute Technology Press , 2016 . (in Chinese)

CATTAFESTA L , SHEPLAK M . Actuators for active flow control [J ] . Annual Review of Fluid Mechanics , 2011 , 43 : 247 - 272 .

杨瑞 , 罗振兵 , 夏智勋 , 等 . 高超声速导弹等离子体合成射流控制数值研究 [J ] . 航空学报 , 2016 , 37 ( 6 ): 1722 - 1732 . DOI: 10.7527/S1000-6893.2016.0028 http://doi.org/10.7527/S1000-6893.2016.0028 快响应控制技术已成为高超声速飞行器发展的关键技术之一,具有极快响应、零质量特性的等离子体合成射流(PSJ)已在超声速流动控制方面初步显示出优异的控制能力,极有潜力应用于高超声速飞行器的快响应控制。基于等离子体合成射流的快响应特性,提出了高超声速飞行器等离子体合成射流快响应控制技术,并通过建立简化的高超声速导弹流场控制模型,对等离子体合成射流控制高超声速导弹进行数值研究。首先,理论分析了高超声速导弹流场的典型结构特征,导弹流场中存在3个特征流场结构。在此基础上,在导弹3个特征位置前面安装等离子体合成射流激励器,研究等离子体合成射流对高超声速流场结构的控制作用,分析由此导致的导弹表面压力分布、升阻特性以及俯仰力矩特性变化。数值仿真结果表明:等离子体合成射流对高超声速导弹外流场中膨胀波和斜激波都具有控制作用,使得波的强度均变弱,且对斜激波的控制效果更为显著;导弹流场结构及气动特性变化具有很强的射流跟随性,射流作用下的导弹流场变化响应时间非常短,仅为0.2 ms;通过合理布置等离子合成射流激励器的位置,可以使得导弹表面压力分布快速改变,从而实现高超声速导弹姿态的快速控制。

YANG R , LUO Z B , XIA Z X , et al . Numerical study of plasma synthetic jet control on hypersonic missile [J ] . Acta Aeronautica et Astronautica Sinica , 2016 , 37 ( 6 ): 1722 - 1732 . (in Chinese) DOI: 10.7527/S1000-6893.2016.0028 http://doi.org/10.7527/S1000-6893.2016.0028 Fast response control technology has become one of the key technologies for hypersonic vehicle development. Plasma synthetic jet (PSJ), which is with fast response and synthetic characteristics, has initially shows excellent potential in terms of hypersonic flow control. A fast response hyper-vehicle control technology based on PSJ is proposed based on PSJ's fast response property and a simplified missile flow field control model for numerical study is established. Theoretical analysis of the typical structure of hypersonic missile flow shows that there are three characteristic flow structures. The PSJ actuators is arranged to these three characteristic positions and the effect on flow structure is observed, which results in the changes of the missile surface pressure distribution, as well as the characteristics of the lift, drag and pitching moments. Numerical simulation results indicate that the jet could have a significant influence on hypersonic flows. It makes the intensity of expansion wave and shock wave weaker, and has more significant effect on shock wave. The change of the flow structure and aerodynamic characteristics has a strong jet following character. That is to say, the flow change response time is very short, which is on the order of 0.2 ms. With rational layout of the actuators' position, quick change in the surface pressure distribution can be achieved for a missile, and thus modulating the missile's attitude can be realized.

程林 , 谭慧俊 . 等离子体合成射流主动流动控制技术实验研究进展 [C ] // 第九届全国流体力学学术会议 . 南京 : 中国力学学会 , 2016 .

CHENG L , TAN H J . Progress of experimental research on active flow control technology of plasma synthetic jet [C ] // Proceedings of the 9th National Fluid Mechanics Academic Conference . Nanjing : The Chinese Society of Theoretical and applied Mechanics , 2016 . (in Chinese)

ANDERSON K . Characterization of spark jet for flight [D ] . New Brunswick, NJ, US : The State University of New Jersey , 2012 .

ANDERSON K , KNIGHT D . Plasma jet for flight control [J ] . AIAA Journal , 2012 , 50 ( 9 ): 1855 - 1872 .

LAAD P A , KNIGHT D D . Hypersonic flow control of kinzhal missile via off-axis, pulsed energy deposition [J ] . Journal of Spacecraft and Rockets , 2022 , 59 ( 3 ): 704 - 716 .

CYBYK B , GROSSMAN K , WILKERSON J . Performance characteristics of the SparkJet flow control actuator [C ] // Proceedings of the 2nd AIAA Flow Control Conference. Portland, OR , US : AIAA , 2004 .

ZHANG W , SHI Z , ZHANG C , et al . A study on flow control in a hypersonic inlet using a plasma synthetic jet actuator [J ] . Physics of Fluids , 2022 , 34 ( 10 ): 106109 .

钟翔宇 , 黄伟 , 钮耀斌 , 等 . 高超声速飞行器激波/边界层干扰控制方法综述 [J ] . 飞航导弹 , 2021 ( 6 ): 42 - 48 .

ZHONG X Y , HUANG W , NIU Y B , et al . Review of shock wave/boundary layer interference control methods for hypersonic vehicles [J ] . Aerodynamic Missile Journal , 2021 ( 6 ): 42 - 48 . (in Chinese)

WANG P , ZHANG X B . Inverse optimal missile guidance law under constraints based on prescribed-time explicit reference governor [J ] . ISA Transactions , 2022 , 129 : 395 - 404 .

WANG P , ZHANG X B , ZHU J H . Integrated missile guidance and control: a novel explicit reference governor using a disturbance observer [J ] . IEEE Transactions on Industrial Electronics , 2019 , 66 ( 7 ): 5487 - 5496 .

崔龙泉 , 周岩 , 谢玮 , 等 . 等离子体合成射流激波-激波干扰控制数值模拟 [J ] . 空军工程大学学报 , 2023 , 24 ( 2 ): 1 - 9 .

CUI L Q , ZHOU Y , XIE W , et al . A numerical simulation in control of shock-shock interference with hypersonic vehicle head by using plasma synthetic jet [J ] . Journal of Air Force Engineering University , 2023 , 24 ( 2 ): 1 - 9 . (in Chinese)

李铮 , 徐聪 , 张健 , 等 . 等离子体合成射流激励器高速流场逆向喷流控制 [J ] . 航空学报 , 2022 , 43 ( 增刊2 ): 225 - 232 .

LI Z , XU C , ZHANG J , et al . Reverse jet flow control by plasma synthetic jet actuator in high speed flow field [J ] . Acta Aeronautica et Astronautica Sinica , 2022 , 43 ( S2 ): 225 - 232 . (in Chinese) DOI: 10.7527/S1000-6893.2022.27789 http://doi.org/10.7527/S1000-6893.2022.27789 As a special aerodynamic phenomenon accompanying high-speed flight， shock wave has an important impact on the safety and performance of aircraft. Effective flow control has great significance in improving the aerodynamic/thermal environment of aircraft. Plasma has attracted more and more attention in recent years because of its simple structure， small mass， fast frequency response， large excitation bandwidth， adjustable excitation intensity， easy arrangement and no auxiliary control system. In this paper， high speed schlieren and laser dynamic pressure sensor are used to study the unsteady control of bow shock by counter jet of plasma synthetic jet. The results show that plasma synthetic jet has a strong flow control effect， whose control time is more than 600 μs. With the decrease of jet pressure， the controlled bow shock presents short penetration mode and long penetration mode changes. The debugging process of the two modes has a certain degree of drag reduction effect on the model.

孙志坤 , 史志伟 , 张伟麟 , 等 . 等离子体激励器对高速翼型升阻特性的影响 [J ] . 航空学报 , 2022 , 43 ( 增刊2 ): 23 - 39 .

SUN Z K , SHI Z W , ZHANG W L , et al . Effect of plasma actuator on lift-drag characteristics of high-speed airfoil [J ] . Acta Aeronautica et Astronautica Sinica , 2022 , 43 ( S2 ): 23 - 39 . (in Chinese) DOI: 10.7527/S1000-6893.2022.27705 http://doi.org/10.7527/S1000-6893.2022.27705 Plasma excitation is widely studied as an active flow control technology with a short response time. Numerical simulations are used to investigate the effects of the actuator cavity， actuator arrangement position， angle of attack， and discharge parameters on improvement in the lift-drag characteristics of hypersonic airfoils. Corresponding experimental validation is conducted. The results show that the cavity of the exciter will generate a drag reduction effect， and the time-average drag reduction effect of the cavity is better than that of the plasma actuator. The decreasing distance of the actuator to the airfoil leading edge leads to stronger improvement in the aerodynamic performance of the airfoil. The hypersonic airfoil leading edge wedge area is the optimum geometric position for the actuator to improve the aerodynamic performance of the airfoil. Increasing the inflow angle of attack reduces the negative effect of the actuator cavity on the airfoil aerodynamic performance when the actuator is in the optimum geometric position， while also impairing the time-average flow control performance of the actuator. In addition， to improve the exciter energy utilization efficiency， the effect of different discharge parameters on the aerodynamic performance improvement of the airfoil is studied. The optimum duty cycle of the plasma synthetic jet exciter for lifting the drag and lift characteristics of hypersonic airfoils is 1.83%. The results provide a reference for the control of hypersonic flow with plasma synthetic jet exciter.

于维鑫 , 朱文超 , 程晓 , 等 . 纳秒脉冲等离子体合成射流激励器的流场特性分析 [J ] . 气体物理 , 2021 , 6 ( 2 ): 38 - 45 .

YU W X , ZHU W C , CHENG X , et al . Analysis of flow field of nanosecond pulsed plasma synthetic jet [J ] . Physics of Gases , 2021 , 6 ( 2 ): 38 - 45 . (in Chinese)

殷宁 , 谭慧俊 , 梁钢 , 等 . 等离子体激励器的静特性与高速特性仿真研究 [J ] . 核聚变与等离子体物理 , 2020 , 40 ( 1 ): 90 - 96 .

YIN N , TAN H J , LIANG G , et al . Investigation on static and high speed characteristic of a plasma actuator [J ] . Nuclear Fusion and Plasma Physics , 2020 , 40 ( 1 ): 90 - 96 . (in Chinese) DOI: 10.16568/j.0254-6086.202001015 http://doi.org/10.16568/j.0254-6086.202001015 A parametric study of high-frequency plasma jet actuator was carried out, using the experiment- tally measured energy distribution law of arc discharge as an ideal heat source. The influence of the exit angle of the actuator on the flow field was explored. The jet flow field characteristics of the spark discharge actuator under supersonic flow ( Ma 0=2.0) were investigated. The results show that the energy density of heat flux increases and the jet front and forward shock wave moves faster with the decrease of discharge region, and the smaller the exit angle of the jet is, the stronger the momentum injection ability of the actuator along the flow direction is. The rule still applies under high-speed air flow conditions. Compared to the static condition, the momentum injection capability of the jet is stronger and the influence domain is larger under supersonic flow conditions.

周岩 , 夏智勋 , 罗振兵 , 等 . 腔体增压等离子体合成射流激励器工作特性 [J ] . 国防科技大学学报 , 2019 , 41 ( 6 ): 12 - 18 .

ZHOU Y , XIA Z X , LUO Z B , et al . Characterization of plasma synthetic jet actuator with cavity pressurization [J ] . Journal of National University of Defense Technology , 2019 , 41 ( 6 ): 12 - 18 . (in Chinese)

史志伟 , 杜海 , 李铮 , 等 . 等离子体流动控制技术原理及典型应用 [J ] . 高压电器 , 2017 , 53 ( 4 ): 72 - 78 .

SHI Z W , DU H , LI Z , et al . Mechanism and applications of plasma flow control technology [J ] . High Voltage Apparatus , 2017 , 53 ( 4 ): 72 - 78 . (in Chinese)

王鹏 , 沈赤兵 . 等离子体合成射流对超声速混合层的混合增强 [J ] . 物理学报 , 2019 , 68 ( 17 ): 165 - 175 .

WANG P , SHEN C B . Mixing enhancement for supersonic mixing layer by using plasma synthetic jet [J ] . Acta Physica Sinica , 2019 , 68 ( 17 ): 165 - 175 . (in Chinese)

程林 , 孙姝 , 谭慧俊 , 等 . 斜孔式等离子体合成射流激励器静特性的实验 [J ] . 航空动力学报 , 2017 , 32 ( 11 ): 2784 - 2790 .

CHENG L , SUN S , TAN H J , et al . Experiment on static characteristics of plasma synthetic jet actuator with oblique orifice [J ] . Journal of Aerospace Power , 2017 , 32 ( 11 ): 2784 - 2790 . (in Chinese)

吴云 , 李应红 . 等离子体流动控制研究进展与展望 [J ] . 航空学报 , 2015 , 36 ( 2 ): 381 - 405 . DOI: 10.7527/S1000-6893.2014.0246 http://doi.org/10.7527/S1000-6893.2014.0246 等离子体流动控制是基于等离子体气动激励的新型主动流动控制技术,具有响应时间短、激励频带宽等显著技术优势,在改善飞行器/发动机空气动力特性方面具有广阔的应用前景,已成为国际上等离子体动力学与空气动力学交叉领域的前沿研究热点。鉴于此,从介质阻挡放电(DBD)、电弧放电等离子体气动激励特性,等离子体气动激励抑制流动分离、控制附面层、控制激波与激波/附面层干扰、控制压气机与涡轮内部流动、控制管道流动和飞行控制等方面,综合评述了国际上等离子体流动控制的研究进展情况;从创新等离子体气动激励方式,揭示等离子体气动激励与复杂流动的非定常耦合机制,突破等离子体流动控制系统关键技术等方面,对未来的发展进行展望。

WU Y , LI Y H . Progress and outlook of plasma flow control [J ] . Acta Aeronautica et Astronautica Sinica , 2015 , 36 ( 2 ): 381 - 405 . (in Chinese) DOI: 10.7527/S1000-6893.2014.0246 http://doi.org/10.7527/S1000-6893.2014.0246 Plasma flow control is a new type of active flow control technology based on plasma aerodynamic actuation which is advantageous of short reactive time and broad bandwidth. The prospect of plasma flow control on improving aircraft/engine performance has made it a hot topic in the cross field of plasma dynamics and aerodynamics. This paper presents a review of the research progress from the aspects of dielectric barrier discharge (DBD) and arc discharge plasma aerodynamic actuation characteristics, boundary layer control, shock wave control and shock wave/boundary layer interaction control, compressor and turbine flow control, pipe flow and flight control. Also, future development of plasma flow control is looked forward in three aspects, i.e., innovation of plasma aerodynamic actuation, revealing the unsteady coupling mechanism of plasma aerodynamic actuation and complex flow, as well as breakthrough of the key technology of plasma flow control system.

宗豪华 , 宋慧敏 , 梁华 , 等 . 纳秒脉冲等离子体合成射流特性实验研究 [J ] . 推进技术 , 2015 ( 10 ): 1474 - 1478 .

ZONG H H , SONG H M , LIANG H , et al . Experimental study on characteristic of nanosecond pulsed plasma synthetic jet [J ] . Journal of Propulsion Technology , 2015 ( 10 ): 1474 - 1478 . (in Chinese)

王林 , 罗振兵 , 夏智勋 , 等 . 等离子体合成射流能量效率及工作特性研究 [J ] . 物理学报 , 2013 ( 12 ): 125201 - 125207 .

WANG L , LUO Z B , XIA Z X , et al . Energy efficiency and performance characteristics of plasma synthetic jet [J ] . Acta Physica Sinica , 2013 ( 12 ): 125201 - 125207 . (in Chinese)

ZONG H H , KOTSONIS M . Effect of velocity ratio on the interaction between plasma synthetic jets and turbulent cross-flow [J ] . Journal of Fluid Mechanics , 2019 , 865 : 928 - 962 .

LI J F , ZHANG X B . A novel model of plasma synthetic jet actuators coupled energy source term model with mechano-acoustical analogy model [J ] . Journal of Physics D: Applied Physics , 2020 , 53 ( 23 ): 235204 .

LI J F , ZHANG X B . A novel three-dimensional center energy deposition model for the hybrid synthetic jet actuator [J ] . International Communications in Heat and Mass Transfer , 2022 , 134 : 106034 .

WANG Z K , ZHANG X B . Research on a novel combined shock control mechanism for thermal protection and drag reduction in hypersonic compressible flow field [J ] . International Journal of Heat and Mass Transfer , 2023 , 201 : 123592 .

周培培 . 横向喷流对鸭式导弹滚转特性影响研究 [J ] . 空气动力学学报 , 2015 ( 4 ): 475 - 480 .

ZHOU P P . Numerical research on lateral jet interaction for a canard missile rolling control [J ] . Acta Aerodynamica Sinica , 2015 ( 4 ): 475 - 480 . (in Chinese)

赵群 . 基于新型主动流动控制技术的推力矢量喷管特性研究 [D ] . 南京 : 南京航空航天大学 , 2020 .

ZHAO Q . Research on thrust vector nozzle based on new methods of active flow control [D ] . Nanjing : Nanjing University of Aeronautics and Astronautics , 2020 . (in Chinese)

马正雪 , 罗振兵 , 赵爱红 , 等 . 高超声速流场等离子体合成射流逆向喷流特性 [J ] . 航空学报 , 2022 , 43 ( 增刊2 ): 192 - 203 .

MA Z X , LUO Z B , ZHAO A H , et al . Reverse jet characteristics of plasma synthetic jet in hypersonic flow field [J ] . Acta Aeronautica et Astronautica Sinica , 2022 , 43 ( S2 ): 192 - 203 . (in Chinese) DOI: 10.7527/S1000-6893.2022.27747 http://doi.org/10.7527/S1000-6893.2022.27747 To study the flow field characteristics of the reverse plasma synthetic jet under hypersonic conditions， experimental and numerical studies were carried out. In the hypersonic incoming flow with Mach number 8， the flow field variation of the reverse plasma synthetic jet was analyzed by comparing the schlieren and exciter outlet pressure monitoring results in the experiment and simulation. It is verified that under hypersonic conditions， the outlet pressure oscillation of the reverse plasma synthesis jet actuator is caused by multiple jets generated by multiple backfilling in the cavity， causing multiple shocks to sweep over the actuator outlet. The plasma synthesis jet increases the mass flow of the gas outside the jet area， while the precursor shock propagating upstream merges with the bow shock wave into a single shock. The vortex rings produced under the action of high-momentum jets， the low-pressure regions created by counter-currents， and the high-temperature low-density plasma jets reduce the local Mach number， resulting in an increase in the shock penetration depth.

WANG H Y , LI J , JIN D , et al . Manipulation of ramp-induced shock wave/boundary layer interaction using a transverse plasma jet array [J ] . International Journal of Heat and Fluid Flow , 2017 , 67 : 133 - 137 .

WANG H Y , LI J , JIN D , et al . Effect of a transverse plasma jet on a shock wave induced by a ramp [J ] . Chinese Journal of Aeronautics , 2017 , 30 ( 6 ): 1854 - 1865 .

周岩 , 刘冰 , 罗振兵 , 等 . 火花放电合成射流与超声速来流相互干扰特性数值模拟研究 [J ] . 空气动力学学报 , 2016 , 34 ( 4 ): 511 - 516 .

ZHOU Y , LIU B , LUO Z B , et al . Numerical simulation of interaction of spark discharge synthetic jet with supersonic flow [J ] . Acta Aerodynamica Sinica , 2016 , 34 ( 4 ): 511 - 516 . (in Chinese)

周岩 . 新型等离子体合成射流及其激波控制特性研究 [D ] . 长沙 : 国防科技大学 , 2018 .

ZHOU Y . Novel plasma synthetic jet and its application in shock wave control [D ] . Changsha : National University of Defense Technology , 2018 . (in Chinese)

ZHOU Y , XIA Z X , LUO Z B , et al . Effect of three-electrode plasma synthetic jet actuator on shock wave control [J ] . Science China Technological Sciences , 2017 , 60 ( 1 ): 146 - 152 .

YANG G , YAO Y F , FANG J , et al . Large-eddy simulation of shock-wave/turbulent boundary layer interaction with and without SparkJet control [J ] . Chinese Journal of Aeronautics , 2016 , 29 ( 3 ): 617 - 629 .

SONG G Z , ZONG H H , LIANG H , et al . Parametric study of high-frequency characteristics of plasma synthetic jet actuator [J ] . Plasma science & technology , 2021 , 23 ( 12 ): 125503 .

HE Y Y , WANG J , CHEN X . Experimental study on characteristics of plasma synthetic jet actuators with different insulating materials [J ] . IEEE Transactions on Plasma Science , 2022 , 50 ( 10 ): 3583 - 3592 .

LI J F , ZHANG X B . Active flow control for supersonic aircraft: a novel hybrid synthetic jet actuator [J ] . Sensors and Actuators A: Physical , 2020 , 302 : 111770 .

ZONG H H , WU Y , SONG H M , et al . Efficiency characteristic of plasma synthetic jet actuator driven by pulsed direct-current discharge [J ] . AIAA Journal , 2016 , 54 ( 11 ): 3409 - 3420 .

ZONG H H . Influence of nondimensional heating volume on efficiency of plasma synthetic jet actuators [J ] . AIAA Journal , 2018 , 56 ( 5 ): 2075 - 2078 .

ZONG H H , KOTSONIS M . Electro-mechanical efficiency of plasma synthetic jet actuator driven by capacitive discharge [J ] . Journal of Physics D: Applied Physics , 2016 , 49 ( 45 ): 455201 .

LIU R B , CHEN Y S , MEI X Y , et al . Study on improving efficiency of a plasma synthetic jet through dynamic pressure supplemental air [J ] . Journal of Physics: Conference Series , 2021 , 1978 ( 1 ): 12005 .

韩磊 , 章程 , 罗振兵 , 等 . 面向等离子体高能合成射流应用的重频脉冲源研制 [J ] . 高电压技术 , 2017 , 43 ( 9 ): 3093 - 3099 .

HAN L , ZHANG C , LUO Z B , et al . Repetitive pulsed generator for high-energy plasma synthetic jet [J ] . High Voltage Engineering , 2017 , 43 ( 9 ): 3093 - 3099 . (in Chinese)

ZONG H H , KOTSONIS M . Realisation of plasma synthetic jet array with a novel sequential discharge [J ] . Sensors and Actuators A: Physical , 2017 , 266 : 314 - 317 .

LIU R B , LIN R X , LIAN G C , et al . Multichannel plasma synthetic jet actuator driven by Marx high-voltage generator [J ] . AIAA Journal , 2021 , 59 ( 9 ): 3417 - 3430 .

WANG L , XIA Z X , LUO Z B , et al . Three-electrode plasma synthetic jet actuator for high-speed flow control [J ] . AIAA Journal , 2014 , 52 ( 4 ): 879 - 882 .

JIN D , CUI W , LI Y H , et al . Characteristics of pulsed plasma synthetic jet and its control effect on supersonic flow [J ] . Chinese Journal of Aeronautics , 2015 , 28 ( 1 ): 66 - 76 .

陈加政 , 胡国暾 , 樊国超 , 等 . 等离子体合成射流对钝头激波的控制与减阻 [J ] . 航空学报 , 2021 , 42 ( 7 ): 314 - 324 .

CHEN J Z , HU G T , FAN G C , et al . Bow shock wave control and drag reduction by plasma synthetic jet [J ] . Acta Aeronautica et Astronautica Sinica , 2021 , 42 ( 7 ): 314 - 324 . (in Chinese)

王宏宇 , 李军 , 金迪 , 等 . 激波/边界层干扰对等离子体合成射流的响应特性 [J ] . 物理学报 , 2017 , 66 ( 8 ): 241 - 253 .

WANG H Y , LI J , JIN D , et al . Response of the shock wave/boundary layer interaction to the plasma synthetic jet [J ] . Acta Physica Sinica , 2017 , 66 ( 8 ): 241 - 253 . (in Chinese)

ZHANG Z B , WU Y , JIA M , et al . MHD-RLC discharge model and the efficiency characteristics of plasma synthetic jet actuator [J ] . Sensors and Actuators A: Physical , 2017 , 261 : 75 - 84 .

ZHANG Z B , ZHANG X N , WU Y , et al . Experimental research on the shock wave control based on one power supply driven plasma synthetic jet actuator array [J ] . Acta Astronautica , 2020 , 171 : 359 - 368 .

ZHANG C , HUANG B D , LUO Z B , et al . Atmospheric-pressure pulsed plasma actuators for flow control: shock wave and vortex characteristics [J ] . Plasma Sources Science & Technology , 2019 , 28 ( 6 ): 64001 .

WANG Z K , ZHANG X B . Parametric research on drag reduction and thermal protection of blunt-body with opposing jets of forward convergent nozzle in supersonic flows [J ] . Acta Astronautica , 2022 , 190 : 218 - 230 .

张小兵 , 薛涛 . 内弹道学发展与展望 [J ] . 南京理工大学学报(自然科学版) , 2023 , 47 ( 4 ): 446 - 460 .

ZHANG X B , XUE T . Developments and prospects of interior ballistics [J ] . Journal of Nanjing University of Science and Technology (Natural Science) , 2023 , 47 ( 4 ): 446 - 460 . (in Chinese)

王渤 , 罗懿 , 薛涛 , 等 . 基于DENN的NSGA-Ⅱ算法的串联多药室火炮内弹道性能优化 [J ] . 弹道学报 , 2023 , 35 ( 2 ): 20 - 27 .

WANG B , LUO Y , XUE T , et al . Optimization of interior ballistic performance of series multi-chamber gun via DENN-based NSGA-Ⅱ algorithm [J ] . Journal of Ballistics , 2023 , 35 ( 2 ): 20 - 27 . (in Chinese)

张小兵 . 枪炮内弹道学 [M ] . 北京 : 北京理工大学出版社 , 2014 .

ZHANG X B . Interior ballistics of guns [M ] . Beijing : Beijing Institute of Technology Press , 2014 . (in Chinese)

翟建 , 张伟伟 , 王焕玲 . 大迎角前体涡控制方法综述 [J ] . 空气动力学学报 , 2017 , 35 ( 3 ): 354 - 367 .

ZHAI J , ZHANG W W , WANG H L . Reviews of forebody vortex control method at high angles of attack [J ] . Acta Aerodynamica Sinica , 2017 , 35 ( 3 ): 354 - 367 . (in Chinese)

NARAYANASWAMY V , RAJA L L , CLEMENS N T . Control of unsteadiness of a shock wave/turbulent boundary layer interaction by using a pulsed-plasma-jet actuator [J ] . Physics of Fluids , 2012 , 24 ( 7 ): 76101 .

EMERICK T , ALI M Y , FOSTER C , et al . SparkJet characterizations in quiescent and supersonic flow fields [J ] . Experiments in Fluids , 2014 , 55 ( 12 ): 1858 .

REEDY T M , KALE N V , DUTTON J C , et al . Experimental characterization of a pulsed plasma jet [J ] . AIAA Journal , 2013 , 51 ( 8 ): 2027 - 2031 .

NARAYANASWAMY V , RAJA L L , CLEMENS N T . Characterization of a high-frequency pulsed-plasma jet actuator for supersonic flow control [J ] . AIAA Journal , 2010 , 48 ( 2 ): 297 - 305 .

GREENE B R , CLEMENS N T , MAGARI P , et al . Control of mean separation in shock boundary layer interaction using pulsed plasma jets [J ] . Shock Waves , 2015 , 25 ( 5 ): 495 - 505 .

NARAYANASWAMY V , RAJA L L , CLEMENS N T . Control of a shock/boundary-layer interaction by using a pulsed-plasma jet actuator [J ] . AIAA Journal , 2012 , 50 ( 1 ): 246 - 249 .

GREENE B R , CLEMENS N T , MAGARI P , et al . Effect of pulsed plasma jets on boundary layer recovery downstream of a reflected shock wave-boundary layer interaction [C ] // Proceedings of the 46th AIAA Plasma dynamics and Lasers Conference. Dallas, TX , US : AIAA , 2015 .

DYGERT J P . Aerodynamic performance of a biologically inspired hybrid plasma-mechanical flow control and sensing device [D ] . Morgantown, WV, US : West Virginia University , 2022 .

BOLITHO M , JACOB J . Thrust vectoring flow control using plasma synthetic jet actuators [C ] // Proceedings of the 46th AIAA Aerospace Sciences Meeting and Exhibit. Reno, NV , US : AIAA , 2008 .

CARUANA D . Plasmas for aerodynamic control [J ] . Plasma Physics and Controlled Fusion , 2010 , 52 ( 12 ): 124045 .

CHEDEVERGNE F , LEON O , BODOC V , et al . Experimental and numerical response of a high-Reynolds-number M =0.6 jet to a Plasma Synthetic Jet actuator [J ] . International Journal of Heat and Fluid Flow , 2015 , 56 : 1 - 15 .

LAURENDEAU F , LEON O , CHEDEVERGNE F , et al . Particle image velocimetry experiment analysis using large-eddy simulation: application to plasma actuators [J ] . AIAA Journal , 2017 , 55 ( 11 ): 3767 - 3780 .

SARY G , DUFOUR G , ROGIER F , et al . Modeling and parametric study of a plasma synthetic jet for flow control [J ] . AIAA Journal , 2014 , 52 ( 8 ): 1591 - 1603 .

CHIATTO M , PALUMBO A , DE L L . A calibrated lumped element model for the prediction of PSJ actuator efficiency performance [J ] . Actuators , 2018 , 7 ( 1 ): 10 .

TRAFICANTE S , DE GIORGI M G , FICARELLA A . Flow separation control on a compressor-stator cascade using plasma actuators and synthetic and continuous jets [J ] . Journal of Aerospace Engineering , 2016 , 29 ( 3 ): 539 .

RUSSELL A , ZARE H , KONTIS K . Joule heating flow control methods for high-speed flows [J ] . Journal of Electrostatics , 2016 , 80 : 34 - 68 .

SHIN J . Characteristics of high speed electro-thermal jet activated by pulsed DC discharge [J ] . Chinese Journal of Aeronautics , 2010 , 23 ( 5 ): 518 - 522 .

GREENBLATT D , WILLIAMS D R . Flow control for unmanned air vehicles [J ] . Annual Review of Fluid Mechanics , 2022 , 54 : 383 - 412 .

XIE W , LUO Z B , HOU L , et al . Characterization of plasma synthetic jet actuator with Laval-shaped exit and application to drag reduction in supersonic flow [J ] . Physics of Fluids , 2021 , 33 ( 9 ): 96104 .

XIE W , LUO Z B , ZHOU Y , et al . Experimental study on plasma synthetic jet for drag reduction in hypersonic flow [J ] . AIAA Journal , 2023 , 61 ( 3 ): 1428 - 1434 .

ZHANG W L , DING B Z , SHI Z W , et al . Investigation of drag reduction mechanism for blunt bodies with plasma spikes [J ] . Physics of Fluids , 2023 , 35 ( 8 ): 86115 .

ZONG H H , CHIATTO M , KOTSONIS M , et al . Plasma synthetic jet actuators for active flow control [J ] . Actuators , 2018 , 7 ( 4 ): 77 .

ZONG H H , VAN T , KOTSONIS M . Airfoil flow separation control with plasma synthetic jets at moderate Reynolds number [J ] . Experiments in Fluids , 2018 , 59 ( 11 ): 169 .

CARUANA D , BARRICAU P , GLEYZES C . Separation control with plasma synthetic jet actuators [J ] . International Journal of Aerodynamics , 2013 , 3 ( 1 ): 71 - 83 .

孙志坤 , 史志伟 , 李铮 , 等 . 逆向等离子体合成射流抑制低速流动分离的研究 [J ] . 力学学报 , 2023 , 55 ( 6 ): 1267 - 1277 .

SUN Z K , SHI Z W , LI Z , et al . Opposing plasma synthetic jet for low-speed flow separation inhibition [J ] . Chinese Journal of Theoretical and Applied Mechanics , 2023 , 55 ( 6 ): 1267 - 1277 . (in Chinese)