基于被动二次流的射流偏转比例控制  

Proportional control of jet deflection with passive secondary flow

作　　者：曹永飞[1] 顾蕴松[1] 程克明[1] 肖中云[2] 陈作斌[2] 何开锋[2] 

机构地区：[1]南京航空航天大学航空宇航学院,南京210016 [2]中国空气动力研究与发展中心计算空气动力研究所,绵阳621000

出　　处：《航空学报》2015年第3期757-763,共7页Acta Aeronautica et Astronautica Sinica

基　　金：江苏省普通高校研究生科研创新计划资助项目(CXLX13_131);中央高校基本科研业务费专项资金资助;江苏高校优势学科建设工程资助项目~~

摘　　要：射流偏转比例控制一直是流体式推力矢量（FTV）技术所追求的目标之一。本文研制了一种二元流体式推力矢量喷管,采用能量消耗极小的被动二次流与Conada壁面相结合的方式对低速主射流进行矢量偏转控制,通过改变喷管控制缝入口面积实现了主射流偏转的连续比例控制。对低速主射流两侧控制缝压力和射流偏转角进行测量,获得了主射流偏转角随两侧控制缝压力差系数变化的控制规律曲线。结果表明：低速主射流最大偏转角达到19°,在偏转范围内控制曲线分为敏感区和迟钝区。敏感区的控制曲线近似线性,斜率较大,范围约为±15°;而迟钝区的控制曲线斜率较小,在两侧15°~19°的范围内。该结果证实了主射流两侧的压力差是造成其偏转的直接原因。The proportional control of jet deflection is always one of the goals of fluidic thrust vectoring（FTV）technology.A two-dimensional new fluidic thrust vectoring nozzle is designed and manufactured.Thrust vector control of the low-speed primary jet is investigated using passive secondary flow and Conada wall surfaces,which has ultra-low energy consumption.The primary jet can be continuously and proportionally vectored by changing the area of entrance of nozzle control slot.The pressure of control slots on both sides and deflection angle of the primary jet are measured;the control curve of the primary jet deflection angle versus the coefficient of pressure difference between control slots is obtained.The results show that the maximum deflection angle of the low-speed primary jet is up to 19°;the control curve is divided into sensitive zone and inert zone in the deflection range.The control curve of sensitive zone is approximately linear with steep slope,within a range of±15°;while the inert zones are from-19°to-15°and from ＋15°to＋19°,where the control curve slope is gentle.The experimental results demonstrate that the pressure difference between both sides of the primary jet is the direct cause of jet deflection.

关 键 词：流体式推力矢量 推力矢量喷管 二次流 流动控制 比例控制 Coanda效应 

分 类 号：V211.71[航空宇航科学与技术—航空宇航推进理论与工程]