火箭级间分离过程流场数值模拟

Numerical Simulation of the Flow Fields for the Stage Separation of the Multi-stage Rocket

火箭级间不同排焰窗位置构型会对级间动态热分离过程产生影响,采用耦合求解轴对称非定常N-S方程与一维分离动力学方程的方法,开展了多个工况的数值仿真,研究了不同排烟窗位置的影响。结果表明,排焰窗位置更加靠近二级火箭时有利于两级火箭在分离过程中获得较高的相对加速度,促进两级火箭的快速分离。但此时级间区域流场在分离过程中存在剧烈震荡的阶段,而当排焰窗位置更加靠近一级火箭时,级间区域流场则相对平稳,一级火箭前封头受力也更加均匀。

Different position of exhaust flame window has a big effect on the multi-stage rocket separation process.Based on the method of the unsteady axisymmetric NS equation coupled with one dimension separation dynamics equation,several cases were numerical simulated to investigate the effects caused by different exhaust flame position.According to the simulation result,when exhaust flame window is close to the second stage rocket,both stages will get a greater acceleration and separate rapidly.Meanwhile,the flow filed features significant oscillation,however,when exhaust flame window is close to the first stage rocket,the flow filed features relatively smooth,and the pressure on the first stage is steady.