基于非结构嵌套网格技术的低空大动压级间分离数值模拟  

Numerical Simulation of Stage 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,北京100076

出　　处：《导弹与航天运载技术》2020年第5期20-24,共5页Missiles and Space Vehicles

摘　　要：为有效预示低空大动压环境下飞行器级间分离过程,利用数值模拟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),仿真给出飞行器高速级间分离过程前后体及流体相互耦合的动态运动过程。结果表明:数值模拟级间分离过程可得到后体和前体清晰、直观的流场特性和分离轨迹、姿态特性;级间分离的流场结构丰富,存在分离区、回流区、高压区等,对前后体气动特性影响较大;依靠后体气动力可实现级间的安全分离,但后体的初始分离抬头趋势明显。To simulate the stage 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 front vehicle and booster’s trajectory,orientation and even flow field can be directly obtained from the simulation;the flow field’s between the front vehicle and booster is filled with shear layer,flow separation,local high pressure,dead water region;With the help of booster’s drag force,the safety separation between stages can be realized,but the initial pitch angle of the of booster is obvious which is a separation safety hazard.

关 键 词：非结构嵌套网格 低空大动压 级间分离 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]