摘要
应用了结构网格中的Chimera重叠网格技术和Favre平均三维N-S方程以获得流场解.采用k-ε湍流模型模拟气体的湍流粘性影响,计算中分别考虑空气和两种火箭发动机喷流等三种不同流动介质,采用时间相关边界模拟发动机拖尾段的非定常流动,最终求解带约束的六自由度弹道方程模拟了导弹助推器的分离脱落过程.并对发动机喷流对助推器分离的影响开展研究.所做工作可对于精确确定火箭助推器分离轨迹及姿态提供方法参考.
The overset/Chimera algorithm for structured grids and Favre-averaged Navier-Stokes equations were employed to solve the flow field. Tstion gas jets, were considered in this simulation. A time profile boundary was employed to simulate the unsteady flow in the tail off duration of the booster. The separating trajectory was ultimately achieved by solving the 6DOF （six degree of freedom） motion models with certain constraints. Moreover, the influence of engine-jet on booster separation was studied. The work provides a reference for accurately simulating the trajectory and attitude of rocket booster.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2008年第2期342-346,共5页
Journal of Aerospace Power
关键词
航空
、航天推进系统
射流
拖尾段
重叠网格
助推器分离
时间相关边界
数值模拟
aerospace propulsion system
engine-jet
tail off duration
overset grid
booster separation
time profile boundary
numerical simulation
