侧向喷流对导弹方向舵局部气动热特性的影响  

Effect of lateral jet on local aerodynamic heating characteristics of missile rudders

作　　者：曾品棚 陈树生 冯聪 杨华 高正红[1] ZENG Pinpeng;CHEN Shusheng;FENG Cong;YANG Hua;GAO Zhenghong(School of Aeronautics,Northwestern Polytechnical University,Xi’an 710072,China;AVIC The First Aircraft Institute,Xi’an 710089,China)

机构地区：[1]西北工业大学航空学院,西安710072 [2]中航工业第一飞机设计研究院,西安710089

出　　处：《空气动力学学报》2023年第9期70-81,共12页Acta Aerodynamica Sinica

基　　金：中国科协青年人才托举工程(2022QNRC001)。

摘　　要：为探索侧向喷流流动控制技术对高速导弹方向舵局部气动热特性的影响规律及相关机理,对带有方向舵和舵轴的导弹在不同攻角和喷流条件下进行了数值模拟,得到了模型流场和壁面热流分布。研究结果表明:喷流压比达到75时,可以避免受弓形激波干扰的来流气体作用在方向舵上,能有效减少方向舵前缘中后段的壁面热流;随着喷口位置与方向舵前缘距离的增加,喷流后回流区结构和范围变化不明显,方向舵前缘的壁面热流变化不大;不同攻角来流条件下,侧向喷流均能有效降低方向舵前缘的壁面热流。攻角大于10°后,喷流的热防护效果有所降低;有攻角来流条件下,在舵轴的正前方喷流,自由来流绕喷流流动,舵轴下壁面边界层内气体密度上升,使舵轴两侧压差增大,舵轴的壁面热流增大;在0°攻角来流条件下,喷口两侧方向舵所受侧向力与喷流推力方向相反,此时导弹的放大因子增大。To explore the effect law and related mechanism of the lateral jet flow control technology on the local aerodynamic heating characteristics of the hypersonic missile rudder,numerical simulations of a missile with are carried out under different incoming flow and jet conditions.When the jet pressure ratio reaches 75,the surface heating flux in the middle and later section of the rudder leading edge can be greatly reduced,as it can avoid the freestream interfered by the bow shock acting on the rudder.With the increase of the distance between the nozzle position and the leading edge of the rudder,the change of the structure and scope of the recirculation zone after the jet is not obvious,and the change of the wall heat flow at the leading edge of the rudder is not significant.Under different angles of attack,lateral jets can effectively reduce the wall heat flow at the leading edge of the rudder.At an angle of attack above 10°,the thermal protection effect of the jet is reduced.Under a certain angle of attack,the jet in front of the rudder shaft causes the freestream to flow around the jet.The gas density within the boundary layer of the lower wall of the rudder shaft increases,which causes a large pressure difference on both sides of the rudder shaft,and leads to an increase of the surface heating flux of the rudder shaft.Under 0°angle-of-attack incoming flow condition,the lateral force of the rudders on both sides of the nozzle is in the same direction as the jet thrust.This causes increasing of the amplification factor of the missile.

关 键 词：侧向喷流 流动干扰 气动热 方向舵 数值模拟 

分 类 号：TJ011.5[兵器科学与技术—兵器发射理论与技术] O357.53[理学—流体力学]