阶梯装药固体火箭发动机点火内流场特性研究

The Study on Ignition Interior Flow Field Characteristics of Ladder-shaped Propellant Solid Rocket Motor

针对两节阶梯装药在火箭弹中的应用,对该类型固体火箭发动机点火内流场特性进行数值模拟。运用FLUENT软件进行二维轴对称非定常数值分析,通过UDF编程,采用表面单元格临界点火准则实现推进剂表面不同部位单元格的燃气加质,计算得到了前后燃烧室的不同部位压力分布及变化情况和点火器喷孔附近的激波传递情况。研究结果表明,该方法能够较好的预示点火内流场的特性,可以为阶梯装药发动机的点火性能研究和点火设计提供理论依据。

According to the application of two step ladder-shaped propellant in solid rocket motor, a numerical simulation was made for the type of solid rocket motor ignition characteristics of interior flow field. The FLUENT software was used to make unsteady two-dimensional axisymmetric numerical simulation, through the UDF programming, the cell surface critical criteria were applied to achieve the surface cells in different parts of the gas increases quality respectively, pressure distribution and variation in different regions of chamber and shock wave transmission near the igniter nozzle were obtained. The result can predict the characteristics of ignition flow field, and provide basis for the ignition study and design of ladder-shaped propellant solid rocket motor.