固体火箭发动机侵蚀燃烧的数值仿真

Numerical Simulation Process of Erosive Burning in a Solid Rocket Motor

固体火箭发动机在燃烧过程中具有随机性和非线性,不能准确建模。为了进一步研究固体火箭发动机侵蚀燃烧,通过fluent计算流体软件和动网格技术,采用推进剂燃烧瞬态模型Zeldovich-Novozhilov能量方程,耦合移动边界,对固体火箭发动机侵蚀燃烧过程进行了轴对称数值仿真,解决了燃面推移非线性问题。得到移动边界条件下瞬态的内流场分布,分析了不同时刻燃烧室内的中心密流、燃烧室直径和侵蚀比在不同位置的变化规律,通过数据拟合出了一个侵蚀燃烧速率显示的表达式。上述研究对发动机工程上的设计有着参考作用,对发动机的试验有参考价值。

In order to further study the erosive burning solid rocket motor, through the FLUENT software and dy namic mesh technique, an axisymmetric numerical simulation method which coupled the propellant combustion model of transient energy equation Zeldovich Novozhilov and a moving boundary was carried out for the unsteady erosion burning process of a solid rocket motor with side burn, to solve nonlinear problem of burning surface moving, the transient flow field distribution in the moving boundary conditions was grained. And the change law of core mass flux, diameter of chamber and erosion ratio were analysed at different times and different positions. An explicit expression of erosive burning was obtained. The research can be a reference for the desin of this twe solid rocket motors.