飞翼布局纵向气动特性的等离子体激励控制  

Longitudinal Aerodynamic Control over Flying Wing Using Plasma Actuators

作　　者：龙玥霄 刘国政[2] 孟宣市[1] 李华星[1] 刘铁中[2] LONG Yuexiao;LIU Guozheng;MENG Xuanshi;LI Huaxing;LIU Tiezhong(School of Aeronautics,Northwestern Polytechnical University,Xi＇an 710072,China;China Aviation Industry Aerodynamics Research Institute Harbin 150001,China)

机构地区：[1]西北工业大学航空学院,西安710072 [2]中国航空工业空气动力研究院,哈尔滨150001

出　　处：《高电压技术》2018年第9期3049-3057,共9页High Voltage Engineering

基　　金：国家自然科学基金(11172243;11672245)~~

摘　　要：为提升飞翼布局飞行器的升/阻力、俯仰力矩和失速特性,利用纳秒脉冲介质阻挡放电等离子体激励对飞翼模型进行控制实验研究,分析激励对全机绕流的控制机理,讨论最佳激励位置。实验在直径1.5 m的低速风洞中进行,风速30 m/s,迎角范围0°～30°。实验结果发现：纳秒脉冲等离子体激励输出纳秒级的脉冲波形,能耗低,其诱导速度几乎为零,快速的瞬时温升产生平面–半球形组合压缩波,该压缩波在20μs内以超音速传播,随后迅速降低至亚音速水平,最终表现为弱的速度扰动;来流速度v∞=30 m/s下,应用纳秒脉冲激励控制飞翼前缘流动分离,全机最大升力系数提高7.5%,失速迎角推迟3°,俯仰力矩系数平均降低11.6%;小迎角下,前缘分离从机翼外侧翼尖部位开始,位于前缘外侧的激励器控制效果明显,随着迎角逐渐增大,分离点位置向机翼上游内侧移动,位于前缘内侧的激励器控制效果明显。实验研究表明纳秒脉冲等离子体激励可有效控制机翼前缘流动分离,提升飞翼布局的全机纵向气动特性及其失速特性。To optimize the lift/drag, pitching moment and stall characteristics of the flying wing, we applied nanosecond pulsed（NS-） dielectric barrier discharge（DBD） plasma actuators to experimentally investigated the control mechanism. The control mechanism of DBD plasma around the wing is concluded and the optimum actuation position is obtained. The experiment was conducted in a low-speed wind tunnel of which inlet diameter is 1.5 m. The test wind speed is 30 m/s and the range of angle of attack is 0°~30°. The results show that NS-DBD periodically outputs nanosecond level pulses with a low energy consumption. The induced velocity of NS-DBD is nearly zero. The rapid temperature rise generates a combined compression wave which consists of a planar wave and a hemispheric wave. The developing speed of the wave can reach a supersonic level within the first 20 μs. Then the speed quickly decreases to subsonic level and finally appears as a weak flow disturbance. By using NS-DBD plasma actuation at 30 m/s, the maximum lift coefficient is increased by 7.5% and the install angle delayed 3°. The pitching moment is decreased by an average of 11.6%. At a low angle, the optimal actuation place is at the outboard of the wing for the reason that the separation begins from the outboard. When the angle of attack increases, the separation position moves upstream. Thus, the optimal actuation place locates at the inboard place. The study indicates that the NS-DBD plasma actuation effectively controls the leading edge separation, and improves the longitudinal aerodynamics and stall characteristics over the flying wing.

关 键 词：飞翼布局 纳秒脉冲 等离子体激励 纵向气动特性 失速特性 

分 类 号：V211[航空宇航科学与技术—航空宇航推进理论与工程]