摘要
为研究子母弹在抛撒时的干扰流场特性,选取多舱段子母弹为计算模型,基于课题组自主开发的非结构混合网格Reynolds平均Navier-Stokes方程求解程序HUNS3D,结合非结构嵌套网格技术,耦合六自由度刚体运动学方程,使用了改进的4阶Adams预估-校正法求解六自由度刚体运动方程.利用跨声速下典型外挂物分离作为验证算例,仿真结果与实验结果高度拟合,验证了求解器的精度.对锁定母弹自由度和释放母弹的自由度两种计算状态进行数值模拟.仿真结果表明:由于激波干涉作用,子弹与母弹之间有较强的耦合作用;释放母弹自由度后,子弹的气动力参数发生了较大变化.
In order to study the disturbance flow field characteristics of the submunition during the dispersal,the multi-cabin submunition was selected as the calculation model,based on the unstructured hybrid grid Reynolds average Navier-Stokes equation solver HUNS3D developed by the research group,combined with the unstructured overset grid technology.The six-degree-of-freedom rigid body kinematics equation was coupled.The six-degree-of-freedom rigid body motion equation was solved by using the improved fourth-order Adams predictor-correction method.Using the typical external object separation under transonic speed as a verification example,the simulation results are highly fitted with the experimental results,and the accuracy of the solver is verified.Then the numerical simulation of the two calculation states of the degree of freedom of locking the projectile and releasing the projectile was carried out.The simulation results show that there is a strong coupling between the submunition and the projectile due to the shock interference.After releasing the freedom of the projectile,the aerodynamic parameters of the submunition have changed greatly.
作者
靳晨晖
王刚
王泽汉
JIN Chen-hui;WANG Gang;WANG Ze-han(School of Aeronautics,Northwestern Polytechnical University,Xi′an 710072,China)
出处
《气体物理》
2018年第4期47-63,共17页
Physics of Gases
关键词
子母弹
非定常
嵌套网格
六自由度
数值模拟
cluster munition
unsteady
overset grid
six degree of freedom
numerical simulation
