基于非结构嵌套网格的低空大动压头罩分离数值模拟  

Numerical Simulation of Shroud Separation with Overset Unstructured Grid in Low Altitude with High Dynamic Pressure

作　　者：袁亚 李冬[1] 马友林[1] 陈皓[1] 王亮[1] Yuan Ya;Li Dong;Ma You-lin;Chen Hao;Wang Liang(China Academy of Launch Vehicle Technology,Beijing,100076)

机构地区：[1]中国运载火箭技术研究院

出　　处：《导弹与航天运载技术》2019年第5期17-22,共6页Missiles and Space Vehicles

摘　　要：为准确模拟低空大动压恶劣环境下头罩分离的全过程,利用多面体非结构动态嵌套网格技术,耦合求解雷诺平均纳维-斯托克斯控制方程(Naiver-Stokes equations, N-S)和六自由度运动方程(6-Degrees of Freedom, 6-DoF),实时计算头罩分离过程中的刚体与流体相互耦合的动态分离运动。结果表明:采用数值模拟方法可得到清晰直观的分离轨迹,同时需合理配置主动分离力大小、作用行程、质心位置才能保证头罩分离安全;随着头罩分离张角的增加,高速气流进入头罩并在头罩和飞行器本体之间的间隙出现"填充-滞止-泄流"流动现象,直接影响头罩气动力变化。To simulate the shroud separation from its initial closed position in low altitude with high dynamic pressure accurately, the CFD(Computational Fluid Dynamics) and OUG(Overset Unstructured Grid) are employed to solve the coupled RANS N-S and 6-DoF functions to simulation the dynamic separation. The simulation result shows that the shroud’s trajectory and orientation can be directly obtained and the separation force needs to be designed properly to ensure the safety of shroud’s movement. The high-speed free stream first filled in the shroud and then stagnated in the back of the shroud until the gap is large enough to release the stagnation flow. The phenomenon induces dramatic change of the shroud and vehicle’s aerodynamic characteristics.

关 键 词：非结构嵌套网格 头罩分离 低空大动压 数值模拟 

分 类 号：V411[航空宇航科学与技术—航空宇航推进理论与工程]