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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.
A small solid propellant rocket with lateral jet was used in the attitude control system to study the numerical simulation of the lateral jet flow field in supersonic / hypersonic flow. By numerical solution of the three-dimensional compressible Navier-Stokes (NS) equation, The effects of the angle of attack, the height, the Mach number, the vacuum thrust of the side-jet engine and the shape of the nozzle on the force / torque magnification factor were studied. The results show that the lateral The interaction between jet flow and inflow causes the structure of the flow field to be very complicated with the interference characteristics such as shock wave, pressure platform effect and surround effect. The angles of attack, the height, the vacuum thrust force of side jet engine and other factors have different force / moment amplification factors Degree of impact.