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为了研究管道火箭几何分布、工作条件及流道几何外形对流场和二次来流引射特性的影响,以含双方程k-ωSST湍流模式的质量平均Navier-Stokes方程为控制方程,对含火箭的管道流场进行了数值模拟,对比研究了管道火箭位置、燃烧室压强对管道流场及二次来流引射特性的影响。结果表明:在管道火箭膨胀喷流没有碰触管道侧壁前,二次来流流量随火箭燃烧室压强的增加而增加,而一旦火箭膨胀喷流边界快速膨胀至流道壁面,被引射来流流量将很难得到进一步增加;随着飞行马赫数的增加,二次来流冲压作用增强,可用来调制管道流场;远场来流静止对应于起飞阶段,正是火箭在最大燃烧室压力(满功率)工作阶段,由此需要较好地解决火箭与管道的尺度匹配问题,否则很难获得相应的增益,内嵌(支板)火箭概念更适用于起飞后的飞行阶段。
In order to study the geometric distribution of pipeline rocket, the working conditions and the influence of geometry of flow channel on the flow field and secondary injection characteristics, the mass-average Navier-Stokes equation with two-equation k-ωSST turbulence model is used as the governing equation, The rocket pipeline flow field is numerically simulated. The effects of the rocket position and the pressure of the combustion chamber on the flow field and the secondary jet launching characteristics are studied. The results show that the flow rate of secondary flow increases with the increase of rocket combustion chamber pressure before the rocket expansion jet flows into the side wall of the pipeline, and once the rocket expansion jet boundary rapidly expands to the flow channel wall, Flow will be difficult to get further increase; with the Mach number flight increases, the secondary flow pressure increases, can be used to modulate the flow field of the pipeline; far off to stop the flow corresponds to the takeoff stage, it is the rocket at maximum chamber pressure (Full power) work stage, which needs to solve the scale matching problem between the rocket and the pipeline well, otherwise it is difficult to obtain the corresponding gain. The embedded (support) rocket concept is more suitable for the post-take-off flight stage.