论文部分内容阅读
为深入研究多喷管液体火箭动力系统尾焰冲击特性,以由多喷管液体火箭动力系统构成的发射平台为研究对象,采用三维N-S方程描述尾焰冲击流动过程,采用Realizable k-ε湍流模型封闭流动方程组,并运用压力的隐式算子分割(PISO)算法进行求解,得到了火箭动力系统尾焰对不同导流面导流槽的冲击流场参数。结果表明:导流面上受冲击影响最大的是沿喷管轴线方向的正冲击区域,且助推器尾焰对导流面的冲击效应相比于芯级更加强烈。锥形导流面对多喷管动力系统尾焰具有很好的引射和导流作用,相比于楔形导流面更能降低尾焰的冲击影响,但会在流场中形成漩涡并卷吸高温燃气,可能对发射系统造成破坏,需要增加相应的热防护措施。
In order to study the impact characteristics of multi-nozzle liquid rocket power system tail flame, a launching platform composed of multi-nozzle liquid propellant rocket system is studied. Three-dimensional Navier-Stokes equations are used to describe the impact process of tail flame. Realizable k-ε turbulence model The flow equations were closed and implicit operator partitioning (PISO) algorithm was used to solve the equations. The impact flow parameters of rocket kinetic tail gas to diversion troughs were obtained. The results show that the most impact area on the guide surface is the positive impact area along the nozzle axis, and the impact of the tail of the booster on the guide surface is stronger than that of the core. Cone-shaped diversion surface has many functions of guiding and guiding the tail of multi-nozzle power system, which can reduce the impact of tail flame more than wedge-shaped guide surface, but it will form vortex and flow in the flow field High-temperature gas, may cause damage to the launch system, the need to increase the corresponding thermal protection measures.