导弹助推器分离过程数值模拟研究  

Numerical simulation and study of the separation process of missile booster

作　　者：王力[1] 谷良贤[1] 

机构地区：[1]西北工业大学航天学院,西安710072

出　　处：《航空动力学报》2008年第2期342-346,共5页Journal of Aerospace Power

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.

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 

分 类 号：V430[航空宇航科学与技术—航空宇航推进理论与工程]