Numerical Analysis of Separation of Supersonic Submunition Based on Nested Grid

被引：0
|
作者：
Zhang M. [1 ]
Jiang Y. [1 ]
Cheng L. [1 ]
Yang H. [1 ]
Liu Q. [2 ]
机构：
[1] School of Aerospace Engineering, Beijing Institute of Technology, Beijing
[2] Beijing Institute of Space Launch Technology, Beijing
来源：
Binggong Xuebao/Acta Armamentarii | 2019年 / 40卷 / 01期
关键词：
6-degree-of-freedom; Computational fluid dynamics; Nested grid; Numerical simulation; Submunition separation;
D O I：
10.3969/j.issn.1000-1093.2019.01.010
中图分类号：
学科分类号：
摘要：
To study the separation flow field and aerodynamic characteristics of supersonic submunition, the nested grid technique and the finite volume method are used to discretize Navier-Stokes equations of three-dimensional viscous compressible flow, and simultaneously solve the kinematic equations and dynamics equations of 6-degree-of-freedom (DOF) rigid body. The 6-DOF rigid body motion is coupled with computational fluid dynamics (CFD) to simulate the separation process of submunition at supersonic speed. The characteristics of flow field in the separation of submunition and its initial separation state (such as initial flight velocity and initial attitude angle, etc) were analyzed. The results show that the nested grid technique can be well used to simulate the complex interferent flow field of supersonic submunition. Under the supersonic separation condition, the higher the initial flight speed is when a submunition is removed from cluster munition, the smaller the separation angle of attack is, and the submunition can be separated more quickly and safely. © 2019, Editorial Board of Acta Armamentarii. All right reserved.
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页码：79 / 88
页数：9
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