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Aerodynamic performance enhancement of a flying wing using nanosecond pulsed DBD plasma actuator

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Chinese Journal of Aeronautics 2015年第2期28卷 377-384页

作者： Han Menghu Li Jun Niu Zhongguo Liang Hua zhao guangyin Hua Weizhuo Science and Technology on Plasma Dynamics Laboratory Air Force Engineering University Aerodynamics Research Institute Aviation Industry Corporation of China

Experimental investigation of aerodynamic control on a 35° swept flying wing by means of nanosecond dielectric barrier discharge （NS-DBD） plasma was carried out at subsonic flow speed of 20-40 m/s, corresponding to Reynolds number of 3.1 × 10^5-6.2× 10^5. In control condition, the plasma actuator was installed symmetrically on the leading edge of the wing. Lift coefficient, drag coefficient, lift-to-drag ratio and pitching moment coefficient were tested with and without control for a range of angles of attack. The tested results indicate that an increase of 14.5% in maximum lift coefficient, a decrease of 34.2% in drag coefficient, an increase of 22.4% in maximum lift-to-drag ratio and an increase of 2° at stall angle of attack could be achieved compared with the baseline case. The effects of pulsed frequency, amplitude and chord Reynolds number were also investigated. And the results revealed that control efficiency demonstrated strong dependence on pulsed fre- quency. Moreover, the results of pitching moment coefficient indicated that the breakdown of lead- ing edge vortices could be delayed by plasma actuator at low pulsed frequencies.

关键词： Dielectric barrier dischargeFlow control Flying wing Nanosecond Plasma

Dynamic stall control over a rotor airfoil based on AC DBD plasma actuation

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Advances in Aerodynamics 2021年第1期3卷 153-165页

作者： guangyin zhao Yong Huang Yongdong Yang Guoqiang Li Hesen Yang State Key Laboratory of Aerodynamics China Aerodynamics Research and Development CenterMianyang 621000China Low Speed Aerodynamics Institute China Aerodynamics Research and Development CenterMianyang 621000China Science and Technology on Plasma Dynamics Laboratory Air Force Engineering UniversityXi’an 710038China.

At present,the control capability of dielectric barrier discharge(DBD)plasma actuation covers the flow velocity range of helicopter’s retreating blades,so it is necessary to extend it to the dynamic stall control of rotor airfoils.A DBD plasma actuator was adopted to control the dynamic stall of an oscillating CRA309 airfoil in this *** effectiveness of alternating current(AC)DBD plasma actuation on reducing the area of lift hysteresis loop of the oscillating airfoil was verified through pressure measurements at a Reynolds number of 5.2×10^(5).The influence of actuation parameters on the airfoil’s lift and moment coefficients was *** steady and unsteady actuation could effectively reduce the hysteresis loop area of the lift *** flow control effect of dynamic stall was strongly dependent on the history of angle of *** with the steady actuation,unsteady actuation had more obvious advantages in dynamic stall control,with reducing the area of lift hysteresis loop by more than 30%.The effects of plasma actuation on the airfoil’s flow field at both upward and downward stages were discussed at last.

关键词： Plasma actuation Flow separation Dynamic stall Hysteresis Dielectric barrier discharge

Experimental study on dynamic stall control based on AC-DBD actuation

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Plasma Science and Technology 2021年第11期23卷 96-109页

作者： Hesen YANG Hua LIANG guangyin zhao Bo WANG Shengwu ZHANG Weiliang KONG Science and Technology on Plasma Dynamics Laboratory Air Force Engineering UniversityXi'an 710038People's Republic of China State Key Laboratory of Aerodynamics China Aerodynamics Research and Development CenterMianyang 621000People's Republic of China National Key Laboratory of Rotorcraft Aeromechanics Nanjing University of Aeronautics and AstronauticsNanjing 210016People's Republic of China Institute of Noise&Vibration Naval University of EngineeringWuhan 430030People's Republic of China Academician Workstation Foundation of the Green Aerotechnics Research Institute of Chonging Jiaotong University Chongqing 401120People's Republic of China

To explore AC-DBD's ability in controlling dynamic stall,a practical SC-1095 airfoil of a helicopter was selected,and systematic wind tunnel experiments were carried out through direct aerodynamic *** effectiveness of dynamic stall control under steady and unsteady actuation is *** influence of parameters such as constant actuation voltage,pulsed actuation voltage,pulsed actuation frequency and duty ratio on dynamic stall control effect is studied under the flow condition of k=0.15 above the airfoil,and the corresponding control mechanism is *** actuation can effectively reduce the hysteresis loop area of dynamic lift,and control the peak drag and moment *** unsteady actuation,there is an optimal duty ratio DC=50%,which has the best effect in improving the lift and drag characteristics,and there is a threshold of pulsed actuation voltage in dynamic stall *** optimal dimensionless frequency will not be found;different F+have different control advantages in different aerodynamic coefficients of different pitching *** actuation has obvious control advantages in improving the lift-drag characteristics and hysteresis,while steady actuation can better control the large nose-down moment.

关键词： dynamic stall plasma flow control AC-DBD parameter control law

Rotor performance enhancement by alternating current dielectric barrier discharge plasma actuation

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Plasma Science and Technology 2023年第1期25卷 120-127页

作者：赵光银王畅杨永东李国强史喆羽 China Aerodynamics Research and Development Center Low Speed Aerodynamics InstituteMianyang 621000People's Republic of China

An experimental system was established to explore the plasma flow control effect for helicopter rotors in hover *** the plasma actuator applied at the leading edge of the rotor blades,alternating current dielectric barrier discharge(AC-DBD) plasma actuation was generated by a sinusoidal AC high-voltage *** direct force measurement,the influence of actuation parameters on the aerodynamic performance of the rotor was investigated at a tip Reynolds number of 1.7 × ***-DBD actuation can delay the blade stall to more than 3° with a 20%increase of about in the thrust coefficient at the post-stall *** a constant motor power driving the rotor,AC-DBD actuation could reduce the rotor’s torque at the stalled pitch and increase the rotational speed of the ***,AC-DBD actuation could maintain a relatively high hover efficiency of the rotor at large collective *** a wide range of actuation parameters,AC-DBD plasma actuation could improve the rotor’s aerodynamic performance at large blade ***-speed photography of the tuft motion on the blade’s upper surface showed that AC-DBD plasma actuation could promote the reattachment of the blade’s separation flow.

关键词： rotor flow control plasma actuator dielectric barrier discharge force measurement

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三角翼DBD等离子体流动控制研究进展

航空学报 2019年第3期40卷 33-47页

作者：牛中国赵光银梁华柳平空军工程大学航空工程学院等离子体动力学重点实验室西安710038 重庆交通大学航空学院重庆400074

现代战机采用较多的三角翼,在大迎角绕流时存在前缘涡破裂等气动问题。作为新型主动流动控制技术,等离子体激励频带宽、响应快、结构简单、便于闭环控制,在解决三角翼气动问题上具有潜力。回顾了介质阻挡放电(DBD)等离子体气动激励的基... 详细信息

现代战机采用较多的三角翼,在大迎角绕流时存在前缘涡破裂等气动问题。作为新型主动流动控制技术,等离子体激励频带宽、响应快、结构简单、便于闭环控制,在解决三角翼气动问题上具有潜力。回顾了介质阻挡放电(DBD)等离子体气动激励的基本原理,及其用于三角翼前缘涡控制的研究进展。从来流条件、几何构型、激励参数等方面分析了DBD等离子体激励对流动控制效果的影响规律;结合不同激励频率下流场演化特性,分析了流动控制机理。最后,从理论研究和工程应用的角度,对三角翼前缘涡控制的发展进行总结展望。

关键词：等离子体激励介质阻挡放电流动控制三角翼前缘涡

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翼型动态失速影响因素及流动控制研究进展

航空学报 2020年第8期41卷 119-144页

作者：杨鹤森赵光银梁华王博空军工程大学等离子体动力学重点实验室西安710038 中国空气动力研究与发展中心空气动力学国家重点实验室绵阳621000 南京航空航天大学直升机旋翼动力学国家级重点实验室南京210016

深入认识翼型动态失速,结合有效流动控制手段,对解决直升机、风力机桨叶等动态失速引起的高阻力、大低头力矩等气动问题具有重要意义。本文首先介绍了翼型动态失速的流场特点和危害,进而分析了缩减频率、雷诺数、马赫数以及翼型型面等... 详细信息

深入认识翼型动态失速,结合有效流动控制手段,对解决直升机、风力机桨叶等动态失速引起的高阻力、大低头力矩等气动问题具有重要意义。本文首先介绍了翼型动态失速的流场特点和危害,进而分析了缩减频率、雷诺数、马赫数以及翼型型面等参数对动态失速的影响,并在此基础上总结了常见的动态失速流动控制方法及其研究进展。等离子体气动激励易于产生快速、可控的宽频带气动激励,在动态失速控制领域具有潜力,本文着重介绍了等离子体气动激励动态失速控制的概念和流动控制原理,总结了近来年等离子体激励在翼型动态失速控制上的进展。

关键词：动态失速影响因素流动控制翼型等离子体激励

花蜜中酚类物质对群落中同花期植物传粉的影响

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生态学报 2013年第1期33卷 89-96页

作者：赵广印李建军高洁中国科学院西双版纳热带植物园昆明650223 中国科学院研究生院北京100049

显花植物分泌花蜜以奖励传粉昆虫为其提供的传粉服务。许多植物分泌的花蜜中除了糖和氨基酸等物质外,还含有与植物抗虫有关的次生代谢物质,如生物碱和多酚。饲喂试验表明传粉蜂类偏爱采集含有这些次生代谢物质的花蜜。因此,花蜜中的次... 详细信息

显花植物分泌花蜜以奖励传粉昆虫为其提供的传粉服务。许多植物分泌的花蜜中除了糖和氨基酸等物质外,还含有与植物抗虫有关的次生代谢物质,如生物碱和多酚。饲喂试验表明传粉蜂类偏爱采集含有这些次生代谢物质的花蜜。因此,花蜜中的次生代谢物质对分泌这类花蜜的植物传粉具有进化和生态上的意义。但是,花蜜中的次生代谢物质是否会影响群落中其它同花期植物的传粉尚不清楚。在2009年3—5月份,在西双版纳永久样地就中华蜜蜂(Apis cerana)的传粉行为进行研究,比较了两种饲喂条件下,整个蜂群采集花蜜的花粉种类和单个采集蜂携带的花粉团的花粉种类,以及采集蜂蜜囊中花蜜的含糖量(一组饲喂30%蔗糖糖浆,以下简称"喂纯糖浆组"另一组饲喂同样糖浆但含有0.01%槲皮素,以下简称"喂酚糖浆组")。研究结果表明:饲喂两种不同糖浆的蜂群拜访的植物种类数量上没有明显差异。但是,两组采集工蜂所选择采集植物花粉种类却存在明显差异,它们采集的花粉都包含了一些特有的花粉种类。另外,两组采集工蜂所采集含有2种以上花粉种类花粉团的蜜蜂数量存在明显差异,喂酚糖浆组明显高于饲喂纯糖浆组。两组工蜂蜜囊中花蜜的含糖量也存在显著差异,喂酚糖浆组工蜂蜜囊中花蜜的含糖量明显高于喂纯糖浆组。因此,喂酚糖浆组的工蜂拜访植物的专一性比较低,在一次采集过程中倾向拜访花蜜中含糖量高的植物。花蜜中酚类物质增加了群落中同花期植物之间的花粉传播,从而降低了整个群落的传粉效率。

关键词：花蜜次生代谢物质中华蜜蜂选择行为群落传粉

参数化纳秒脉冲电源激励下表面介质阻挡放电特性

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高电压技术 2019年第10期45卷 3365-3374页

作者：陈杰梁华魏彪赵光银苏志空军工程大学等离子体动力学重点实验室

为研究纳秒脉冲电压上升沿、下降沿、脉宽、以及覆盖电极宽度对表面介质阻挡放电特性的影响。结合放电图像、电压-电流波形以及高速纹影详细分析了各参数对纳秒脉冲表面介质阻挡放电的放电形态、能量消耗以及诱导流场的影响。实验结果表... 详细信息

为研究纳秒脉冲电压上升沿、下降沿、脉宽、以及覆盖电极宽度对表面介质阻挡放电特性的影响。结合放电图像、电压-电流波形以及高速纹影详细分析了各参数对纳秒脉冲表面介质阻挡放电的放电形态、能量消耗以及诱导流场的影响。实验结果表明:脉冲电压上升沿与下降沿时间对放电细丝的均匀性有影响,而放电细丝的长度受脉宽影响较大,同时也受到覆盖电极宽度的制约;纳秒脉冲激励产生冲击波的同时会诱导产生速度较小的弱射流,且射流方向受到各电参数的影响,因此,纳秒脉冲激励不只是单纯的快速加热,还有体积力的作用。

关键词：表面介质阻挡放电上升沿下降沿脉宽电极宽度

NS-DBD激励控制非细长三角翼前缘涡仿真研究

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航空动力学报 2019年第2期34卷 423-433页

作者：赵光银梁华牛中国王学德空军工程大学航空工程学院航空等离子体动力学实验室西安710038 中国航空工业集团有限公司空气动力研究院哈尔滨150001

通过在三角翼前缘施加纳秒脉冲介质阻挡放电(NS-DBD)激励唯象学模型,进行了47°后掠角钝前缘三角翼流动控制的仿真。分析了不同迎角下升力和阻力系数的变化、流场结构的变化、以及激励诱导旋涡的演化过程。研究表明:施加无量纲激励频率F... 详细信息

通过在三角翼前缘施加纳秒脉冲介质阻挡放电(NS-DBD)激励唯象学模型,进行了47°后掠角钝前缘三角翼流动控制的仿真。分析了不同迎角下升力和阻力系数的变化、流场结构的变化、以及激励诱导旋涡的演化过程。研究表明:施加无量纲激励频率F+=1.44的NS-DBD激励后,可明显提高三角翼失速前后的升力系数;同时阻力系数也有所增加,变化趋势与实验结果一致。激励在前缘分离剪切层处诱导产生流向涡,改变了前缘剪切层结构,使其向内卷吸;激励后时均流场形成了明显的负压峰值,前缘涡附着线外移,吸力面回流区减小。

关键词：等离子体前缘涡三角翼流动控制纳秒脉冲介质阻挡放电