超声速/高超声速来流中侧向喷流干扰流场数值模拟  

Numerical simulation of lateral jet interaction flow field in supersonic/hypersonic flow

作　　者：杨希祥[1] 费阳[1] 江振宇[1] 张为华 

机构地区：[1]国防科学技术大学航天与材料工程学院,长沙410073

出　　处：《航空动力学报》2010年第11期2437-2442,共6页Journal of Aerospace Power

基　　金：国家部委基金(2006AAX0X106)

摘　　要：针对姿态控制系统采用侧向喷流的小型固体运载火箭,开展超声速/高超声速来流中侧向喷流干扰流场数值模拟研究.通过数值求解三维可压缩Navier-Stokes(N-S)方程,模拟了侧向喷流干扰流场,分析了干扰流场结构,研究了攻角、高度、马赫数、侧喷发动机真空推力、喷口形状等因素对力/力矩放大因子的影响.研究结果标明,侧向喷流与来流相互作用,使流场结构十分复杂,存在激波、压力平台效应和环绕效应等干扰特性,攻角、高度、侧喷发动机真空推力等因素对力/力矩放大因子均存在不同程度影响.For the small solid launch vehicle using lateral jet as attitude control system,a numerical simulation of the interaction flow field of lateral jet in supersonic/hypersonic flow was conducted.The interaction flow field was simulated by solving the 3-D compressible Navier-Stokes（N-S） equations,the interaction field structure was analyzed,and the interaction effect of some important factors on thrust and moment amplification factor was researched,including attack angle,flight height,Mach number,vacuum thrust of lateral jet thrusters and the nozzle configuration.Research results show that,interaction field structure is very complex,including phenomenon of shock,pressure platform effect and surrounding effect,while attack angle,flight height,Mach number and vacuum thrust of lateral jet thrusters have influence on the thrust and moment amplification factor.

关 键 词：超声速/高超声速流 侧向喷流 干扰流场 数值模拟 放大因子 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程]