固体火箭尾焰等离子体特性影响因素数值

为研究固体火箭尾焰等离子体分布特性，采用CFD方法对不同工况下某型号固体火箭发动机尾焰进行了仿真，获得了尾焰流场温度及压强分布，并采用等离子体浓度模型计算了尾焰等离子体浓度分布。在此基础上，对尾焰等离子体频率进行了求解和分析，得到了其在尾焰轴线方向上的变化规律。分析结果表明，火箭尾焰等离子体特性对推进剂中Al含量的依赖性很高，随着推进剂中Al含量增加，尾焰温度升高，燃气电离度增加直至成为等离子体，尾焰等离子体区域范围增大；随着飞行高度的增加，尾焰等离子体区域位置后移。

Numerical Study on Factors Affecting Plasma Characteristics of Solid Propellant Rocket Exhaust Plume

To study the plasma distribution characteristics of solid propellant rocket exhaust plume, the CFD method was used to simulate the exhaust plume of a solid propellant rocket engine under different working conditions. The temperature and pressure distribution of the plume flow field was obtained, and the plasma concentration distribution of the plume was calculated by plasma concentration model. On this basis, the plume plasma frequency was calculated and analyzed, and the variation law in the direction of the plume axis was obtained. The analysis results show that the plasma characteristics of the rocket exhaust plume are highly dependent on the Al content in the propellant. As the Al content of the propellant increases, the temperature of the plume increases, the gas ionization increases until it becomes the plasma, and the area of the plasma zone is increased; as the flying height increases, the position of the exhaust plume plasma zone moves back.