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Supervised by Ministry of Industry and Information Technology of The People's Republic of China Sponsored by Harbin Institute of Technology Editor-in-chief Yu Zhou ISSNISSN 1005-9113 CNCN 23-1378/T

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Related citation:Juan Duan,Yongliang Xiong,Ningdong Hu.On the Transient Numerical Simulation of Solid Rocket Motor by Coupling Quasi One-Dimension Internal Flow with Three- Dimension Propellant Grain Burnback[J].Journal of Harbin Institute Of Technology(New Series),2021,28(5):15-27.DOI:10.11916/j.issn.1005-9113.19098.
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On the Transient Numerical Simulation of Solid Rocket Motor by Coupling Quasi One-Dimension Internal Flow with Three- Dimension Propellant Grain Burnback
Author NameAffiliation
Juan Duan Department of Mechanics, Huazhong University of Science and Technology, Wuhan 430074, China
Hubei Key Laboratory of Engineering Structural Analysis and Safety Assessment, Wuhan 430074, China 
Yongliang Xiong Department of Mechanics, Huazhong University of Science and Technology, Wuhan 430074, China
Hubei Key Laboratory of Engineering Structural Analysis and Safety Assessment, Wuhan 430074, China 
Ningdong Hu Department of Mechanics, Huazhong University of Science and Technology, Wuhan 430074, China
Hubei Key Laboratory of Engineering Structural Analysis and Safety Assessment, Wuhan 430074, China 
Abstract:
The quasi one-dimension compressible flowfield coupled to the three-dimension propellant grain regression solved by the level-set method was used to simulate the transient internal ballistics of solid rocket motor. One-dimension flowfield instead of three-dimension can save computational cost on the premise of calculation accuracy because the radial and azimuthal variations parameters have little contribution to the internal flowfield. The grain regression in real-time could provide accurate geometrical information for simulation. A combination of flowfluid solver and grain regression can reappear in a relatively real internal ballistic flowfield, so it is good for further studying the instability of solid rocket motor. For level-set equations, the total variation-diminishing second-order Runge-Kutta method for temporal derivatives and a fifth-order weighted-essentially-non-oscillatory scheme for spatial derivatives were used. The total variation-diminishing MacCormack method was used to discrete the Euler equations in flowfield solver. Two modules of this code were tested in this study: one is the burning rate module and the other is the nozzle erosion module. Results show that the burning rate influenced the solid rocket motor efficiency, and the velocity profile in the chamber was affected by the nozzle shape, and the nozzle erosion could influence the head-end pressure spike.
Key words:  transient compressible solver  internal ballistics simulation  level-set method  solid rocket motor
DOI:10.11916/j.issn.1005-9113.19098
Clc Number:V11
Fund:
Descriptions in Chinese:
  

固体火箭发动机内三维药柱燃烧的瞬态拟一维流场仿真

段娟1,2,熊永亮1,2,胡宁东1,2

(1.华中科技大学 力学系,武汉 430074;

2.湖北省工程结构分析与安全评定重点实验室,武汉 430074)

创新点说明:

开发了固体火箭发动机内弹道混合维度求解器——耦合三维水平集法与一维TVD-MacCormack法降阶求解三维固体药柱燃烧退移时的瞬态流场及主要性能参数,该求解器可计算出较高精度的流场参数。

研究目的:

利用拟一维可压缩流场代替三维瞬态流场,并耦合三维水平集法从而降低固体发动机瞬态仿真的计算量,为进一步研究与指导设计提供可行性指导。

研究方法:

文中利用水平集法来捕捉三维药柱的实时界面并以此确定流场计算域,同时利用一维流场代替三维流场可大大节省计算成本,其原理是因为在药柱燃烧过程中径向和周向的流场参数变化对内部流场的影响相对较小。水平集法利用五阶WENO格式的有限差分进行离散,一维流场使用TVD-MacCormack法进行求解。耦合方法中考虑了药柱燃烧速率和喉部烧蚀对流场参数的影响。

结果与结论:

使用三维水平集耦合一维流场法可以准确高效地计算出药柱退移过程中的流场参数。为实际三维发动机整体工作过程仿真提供可行性实施方案。

关键词:瞬态可压缩流场求解器,固体火箭发动机内弹道仿真,水平集法,固体火箭发动机

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