等离子体无人机失速分离控制飞行试验
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摘要
为了进一步推动等离子体流动控制技术工程化应用发展,以无人机机翼失速分离控制为研究对象,以压力及姿态角传感器为测试手段,搭建了飞行验证平台,开展了等离子体无人机(UAV)飞行试验,在真实大气环境下考核了对称布局等离子体激励器的控制能力,建立了从基础研究到工程应用的桥梁。结果表明:当在单侧机翼施加控制时,等离子体激励器能够较好地抑制无人机单侧机翼大迎角失速分离,使得该飞机产生较大的滚转角,从而实现对飞机姿态的控制。该结果为实现等离子体流动控制技术的工程应用积累了技术基础。
To boost the development of application of flow control technology using plasma actuator,aplatform for flight test is established and the Unmanned Aerial Vehicle(UAV)flight test is carried out to evaluate the control effect of symmetrical plasma actuators using pressure sensors and attitude angle sensor in realistic environment.The results indicate that flow separation around one wing of the UAV is suppressed by one symmetrical plasma actuator,and a large roll angle of the UAV is generated.Thus,the attitude control of aircraft is realized by using plasma actuator.The research can lay the foundation for the application of the plasma flow control technology.
To boost the development of application of flow control technology using plasma actuator,aplatform for flight test is established and the Unmanned Aerial Vehicle(UAV)flight test is carried out to evaluate the control effect of symmetrical plasma actuators using pressure sensors and attitude angle sensor in realistic environment.The results indicate that flow separation around one wing of the UAV is suppressed by one symmetrical plasma actuator,and a large roll angle of the UAV is generated.Thus,the attitude control of aircraft is realized by using plasma actuator.The research can lay the foundation for the application of the plasma flow control technology.
引文
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[16]朱益飞,吴云,崔巍,等.大气压空气纳秒脉冲等离子体气动激励特性数值模拟与实验验证[J].航空学报,2013,34(9):2081-2091.ZHU Y F,WU Y,CUI W,et al.Numerical simulation and experimental validation of pulsed nanosecond plasma aerodynamic actuation in air under atmospheric pressure[J].Acta Aeronautica et Astronautica Sinica,2013,34(9):2081-2091(in Chinese).
[17]王林,夏智勋,罗振兵,等.两电极等离子体合成射流激励器工作特性研究[J].物理学报,2014,63(19):194702.WANG L,XIA Z X,LUO Z B,et al.Experimental study on the characteristics of a two-electrode plasma synthetic jet actuator[J].Acta Physica Sinica,2014,63(19):194702(in Chinese).
[18]LIU Z F,WANG L Z,FU S.Study of flow induced by sine wave and saw tooth plasma actuators[J].Science China Physics,Mechanics&Astronomy,2011,54(11):2033-2039.
[19]NIE C Q,LI G,ZHU J Q.Investigation of dielectric bar-rier discharge plasma flow control[J].Science China Physics,Mechanics&Astronomy,2008,51(7):1064-1072.
[20]ZHANG X,HUANG Y,WANG W B,et al.Unmanned air vehicle flow separation control using dielectric barrier discharge plasma at high wind speed[J].Science China Physics,Mechanics&Astronomy,2014,57(6):1160-1168.
[21]ROTH J R,SHERMAN D M,WILKINSON S P.Boundary layer flow control with a one atmosphere uniform glow discharge plasma[C]∥36th Aerospace Sciences Meeting and Exhibit.Reston,VA:AIAA,1998:1-28.
[22]SIDORENKO A A,BUDOVSKY A D,PUSHKAREV A V.Flight testing of DBD plasma separation control system[C]∥46th Aerospace Sciences Meeting and Exhibit.Reston,VA:AIAA,2008:1-9.
[23]FRIEDRICHS W.Unmanned aerial vehicle for flow control experiments with dielectric barrier discharge plasma actuators[D].Darmstadt:Technical University of Darmstadt,2014.
[24]ZHANG X,LI H X,HUANG Y.Wing flow separation control using asymmetrical and symmetrical plasma actuator[J].Journal of Aircraft,2017,54(1):301-309.
[2]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.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).
[3]WANG J J,CHOI K S,FENG L H,et al.Recent developments in DBD plasma flow control[J].Progress in Aerospace Sciences,2013,62(4):52-78.
[4]ZHANG P F,LIU A B,WANG J J.Aerodynamic modification of a NACA 0012aerofoil by trailing-edge plasma Gurney flap[J].AIAA Journal,2009,47(10):2467-2474.
[5]车学科,聂万胜,侯志勇,等.地面实验模拟高空等离子体流动控制效果[J].航空学报,2015,36(2):441-448.CHE X K,NIE W S,HOU Z Y,et al.High altitude plasma flow control simulation through ground experiment[J].Acta Aeronautica et Astronautica Sinica,2015,36(2):441-448(in Chinese).
[6]CHE X K,SHAO T,NIE W S,et al.Numerical simulation on a nanosecond-pulse surface dielectric barrier discharge actuator in near space[J].Journal of Physics D:Applied Physics,2012,45:145201.
[7]史志伟,范本根.不同结构等离子体激励器的流场特性实验研究[J].航空学报,2011,32(9):1583-1589.SHI Z W,FAN B G.Experimental study on flow control characteristics of different plasma actuator[J].Acta Aeronautica et Astronautica Sinica,2011,32(9):1583-1589(in Chinese).
[8]杜海,史志伟,耿玺.等离子体激励器对微型飞行器横航向气动力矩控制的实验研究[J].航空学报,2012,33(10):1781-1790.DU H,SHI Z W,GENG X.Experimental study of directional-lateral aerodynamic moment control of micro air vehicle by plasma actuator[J].Acta Aeronautica et Astronautica Sinica,2012,33(10):1781-1790(in Chinese).
[9]FENG L H,JUKES T N,CHOI K S.Flow control over a NACA 0012aerofoil using dielectric barrier discharge plasma actuator with a Gurney flap[J].Experimental in Fluids,2012,52:1533-1546.
[10]孟宣市,李华星,唐花蕊,等.不同迎角下前体涡流动的等离子体控制特性[J].西北工业大学学报,2012,30(3):402-406.MENG X S,LI H X,TANG H R,et al.Exploring flow features of conical forebody versus angle of attack under plasma actuation[J].Journal of Northwestern Polytechnical University,2012,30(3):402-406(in Chinese).
[11]孟宣市,郭志鑫,罗时钧,等.细长圆锥前体非对称涡流场的等离子体控制[J].航空学报,2010,3(3):500-505.MENG X S,GUO Z X,LUO S J,et al.Control of asymmetric vortices over a slender conical forebody using plasma actuator[J].Acta Aeronautica et Astronautica Sinica,2010,3(3):500-505(in Chinese).
[12]林麒,黄印阳,潘波,等.新型等离子体主动流动控制器及其诱导流场研究[J].空气动力学学报,2012,30(3):312-317.LIN Q,HUANG Y Y,PAN B,et al.Investigation on new-style plasma active flow controllers and its induced flow field[J].Acta Aerodynamica Sinica,2012,30(3):312-317(in Chinese).
[13]潘波,沈锦明,林麒.等离子体激励器流场测量及诱导推力实验[J].推进技术,2011,32(1):146-150.PAN B,SHEN J M,LIN Q.Experiment on flow field and thrust induced by plasma actuator[J].Journal of Propulsion Technology,2011,32(1):146-150(in Chinese).
[14]WU Y,LI Y H,JIA M.Experimental investigation into characteristics of plasma aerodynamic actuation generated by dielectric barrier discharge[J].Chinese Journal of Aeronautics,2010,23(1):39-45.
[15]王林,罗振兵,夏智勋.等离子体合成射流能量效率及工作特性研究[J].物理学报,2013,62(12):1-10.WANG L,LUO Z B,XIA Z X.Energy efficiency and performance characteristics of plasma synthetic jet[J].Acta Physica Sinica,2013,62(12):1-10(in Chinese).
[16]朱益飞,吴云,崔巍,等.大气压空气纳秒脉冲等离子体气动激励特性数值模拟与实验验证[J].航空学报,2013,34(9):2081-2091.ZHU Y F,WU Y,CUI W,et al.Numerical simulation and experimental validation of pulsed nanosecond plasma aerodynamic actuation in air under atmospheric pressure[J].Acta Aeronautica et Astronautica Sinica,2013,34(9):2081-2091(in Chinese).
[17]王林,夏智勋,罗振兵,等.两电极等离子体合成射流激励器工作特性研究[J].物理学报,2014,63(19):194702.WANG L,XIA Z X,LUO Z B,et al.Experimental study on the characteristics of a two-electrode plasma synthetic jet actuator[J].Acta Physica Sinica,2014,63(19):194702(in Chinese).
[18]LIU Z F,WANG L Z,FU S.Study of flow induced by sine wave and saw tooth plasma actuators[J].Science China Physics,Mechanics&Astronomy,2011,54(11):2033-2039.
[19]NIE C Q,LI G,ZHU J Q.Investigation of dielectric bar-rier discharge plasma flow control[J].Science China Physics,Mechanics&Astronomy,2008,51(7):1064-1072.
[20]ZHANG X,HUANG Y,WANG W B,et al.Unmanned air vehicle flow separation control using dielectric barrier discharge plasma at high wind speed[J].Science China Physics,Mechanics&Astronomy,2014,57(6):1160-1168.
[21]ROTH J R,SHERMAN D M,WILKINSON S P.Boundary layer flow control with a one atmosphere uniform glow discharge plasma[C]∥36th Aerospace Sciences Meeting and Exhibit.Reston,VA:AIAA,1998:1-28.
[22]SIDORENKO A A,BUDOVSKY A D,PUSHKAREV A V.Flight testing of DBD plasma separation control system[C]∥46th Aerospace Sciences Meeting and Exhibit.Reston,VA:AIAA,2008:1-9.
[23]FRIEDRICHS W.Unmanned aerial vehicle for flow control experiments with dielectric barrier discharge plasma actuators[D].Darmstadt:Technical University of Darmstadt,2014.
[24]ZHANG X,LI H X,HUANG Y.Wing flow separation control using asymmetrical and symmetrical plasma actuator[J].Journal of Aircraft,2017,54(1):301-309.