以减缓在起降阶段阵风对飞机影响为目标，以GAW-1翼型为研究对象，采用测力、测压、高速PIV (Particle Image Velocimetry)三种研究手段，开展了基于对称布局介质阻挡放电等离子体激励器的阵风减缓风洞实验研究，定量评估了等离子体阵风减缓效果，揭示了等离子体流动控制机理。实验时，将单个对称布局激励器布置在翼型前缘，激励器会诱导产生两股速度近似相等，方向相反的准定常射流。结果表明：1）在阵风环境下，等离子体激励器能够抑制翼型失速分离，推迟失速迎角；施加激励后，失速迎角推迟了2°，最大升力系数提升了12%；2）等离子体激励器能够抑制阵风引起的压力振荡，从而减缓阵风影响；3）对称等离子体激励器诱导产生的展向涡与壁面附近的拟序结构是实现阵风减缓的关键。基于等离子体激励的阵风减缓过程可以分为三个阶段。在第一阶段，一系列诱导涡能够促进壁面附近低能量气流与主流之间的掺混，从而向边界层注入动量。在第二阶段，等离子体诱导涡与来流相互耦合，产生了一个相对封闭的区域，形成了虚拟形变，从而改变了翼型前缘形状。在第三阶段，壁面拟序结构将诱导动量从翼型前缘输运到翼型后缘。研究结果为建立基于等离子体激励的无人机阵风减缓技术提供了方法支撑。

Motivated by the demand of alleviating the impact of gusts during aircraft takeoff and landing, experimental investiga-tions on an airfoil of GAW-1 gust alleviation using a symmetrical plasma actuator were carried out in a low-speed wind tunnel with the help of force measurement, pressure measurement, and high-speed Particle Image Velocimetry (PIV). The effect of gust alleviation using the plasma actuator was quantitatively evaluated, and the control mechanism of was revealed. The symmetrical plasma actuator which can be capable of producing a bi-direction quasi-wall jet with approx-imately equal velocities was mounted at the leading-edge of airfoil. The results indicated that the separation flow around the airfoil can be suppressed and the stall angle of attack can be delayed by the plasma actuator under the gust envi-ronment. The stall angle of attack was delayed by 2 degrees and the maximum lift coefficient was increased by 12% after plasma actuation. Meanwhile, the pressure oscillations caused by gusts can be suppressed by the plasma actua-tor, leading to the gust alleviation. Two typical flow structures, namely spanwise vortices and coherent structures are generated by the plasma actuator. The induced spanwise vortices near the leading-edge of airfoil and the induced co-herent structures in the vicinity of the wall surface play an important role in the gust alleviation. The process of gust alleviation based on plasma actuation can be divided into three stages. Initially, the induced vortices can promote the mixing between low-energy airflow near the wall and the mainstream, thereby injecting momentum into the boundary layer during the first stage. In the second stage, a relatively enclosed region produced by the interaction between the induced vortices and the incoming flow was established and was able to create virtual aero-shaping, thereby changing the shape of the leading edge of the airfoil. Finally, a series of coherent structures transported induced momentum from the leading edge of the airfoil to the trailing edge in the third stage. The present results provide methodological support for establishing the gust alleviation technology for unmanned aerial vehicles based on plasma actuation.