导弹模型后体横向喷流干扰特性  

Transverse jet interaction characteristics on rear section of missile model

作　　者：赖江 赵忠良 李玉平 王晓冰 李浩 LAI Jiang;ZHAO Zhongliang;Li Yuping;WANG Xiaobing;LI Hao(High Speed Aerodynamics Institute,China Aerodynamics Research and Development Center,Mianyang Sichuan 621000,China)

机构地区：[1]中国空气动力研究与发展中心高速空气动力研究所,四川绵阳621000

出　　处：《航空动力学报》2019年第2期469-478,共10页Journal of Aerospace Power

基　　金：国家自然科学基金(11532016);"十三五"装备预研共用技术项目(41401030106)

摘　　要：通过在2m×2m超声速风洞开展横向喷流静态测力和油流显示试验,获取了来流马赫数为1.5～4.0、迎角为-8°～27°、喷流静压比为5～17.6及不同喷口位置等参数对横向喷流干扰的影响规律,结合数值模拟获取了模型表面极限流线和喷口附近干扰流场结构,进而研究了导弹模型强迫运动下的横向喷流干扰特性。结果表明:在模拟参数范围内,位于导弹模型后体的横向喷流均产生有利干扰;来流马赫数越大,干扰放大因子随迎角变化越剧烈,静压比升高导致干扰放大因子减小,"单独向上喷流"干扰程度大于"单独向下喷流";强迫运动条件下基本气动特性和干扰均出现动态迟滞,干扰放大因子尤其在大迎角和下俯过程中明显偏离固定迎角值,表明模型运动对横向喷流干扰特性影响较大。In order to estimate the change in effectiveness of the jet in providing control forces and moments,force-testing and oil-flow tests were carried out in 2 m×2 msupersonic wind tunnel.The effects of a number of parameters such as the angle of attack,jet to crossflow static pressure ratio(PR)and nozzle location,were studied.Mach number ranged from1.5 to 4.0,angle of attack from-8°to 27°,and pressure ratio from 5 to 17.6.Numerical simulation was performed and compared with tests to obtain streamlines on the surface and interaction flowfield near nozzle exit.Pitching motion effect of the missile model on jet interaction was also investigated.Result showed that the effectiveness was enhanced for the conditions considered,as the nozzles were located at the rear body;larger crossflow Mach number resulted in more drastic change with the changing angle of attack.Interaction amplification factors decreased with the increasing PR;upward jet had greater effect than downward jet.In addition,the transverse jet interaction during pitching oscillation was obviously different from the steady interaction,especially during pitching down motion and at high angle of attack.Basic aerodynamic characteristics as well as force and moment amplification factors showed hysteresis properties.Motion effect should be considered when applying the com-bined utilization of transverse jet and traditional fin technique.

关 键 词：导弹模型 横向喷流干扰 超声速 风洞试验 动态气动特性 

分 类 号：V211.7[航空宇航科学与技术—航空宇航推进理论与工程]