变推力固体火箭发动机非稳态影响因素研究

为研究不同因素对喉栓式变推力固体火箭发动机非稳态调节特性的影响,利用Fluent软件的网格动态层变模型,对喉栓匀速调节过程中的内流场进行仿真计算,主要分析了喉栓运动速度、喷管主要结构参数以及推进剂压强指数对非稳态特性的影响.结果表明喉栓运动速度以及推进剂压强指数对非稳态调节特性影响最大,喷管收敛半角对非稳态调节特性影响较小,喉栓半径以及喷管扩张角对非稳态调节特性基本没有影响.

Research on Non-Steady Characters of Thrust Controllable Solid Rocket Motor with Pintle

The pintle controlled solid rocket motor shows distinct non-steady characteristic when nozzle aera is changed by pintle motion. In order to understand the non-steady characteristic, simulation of inflow field during the thrust controlling process with pintle motion was implemented by using the unique dynamic mesh layering model in Fluent software. Velocity of pintle move, nozzle geometry and propellant parameter were investigated as the main influence factors on the non-steady characteristic. It is found that the velocity and pressure index affect the non-steady characteristic greatly, the effect of nozzle convergence half angle on the non-steady characteristic takes the second and expansion half angle and pintle radius have almost no affect to the non-steady characteristic.