Numerical Simulation of Large Sloshing of Propellant in Cylinder Tank of Launch Vehicle

被引：0

作者：

Zhou Q.-Q. ^{[1
]}

Tan Y.-H. ^{[2
]}

Xu Z.-L. ^{[1
]}

Wang J. ^{[3
]}

Wang Z. ^{[3
]}

机构：

[1] State Key Laboratory for Strength and Vibration of Mechanical Structures, School of Aerospace, Xi'an Jiaotong University, Xi'an

[2] Academy of Aerospace Propulsion Technology, Xi'an

[3] Xi'an Aerospace Propulsion Institute, Xi'an

来源：

Tuijin Jishu/Journal of Propulsion Technology | 1600年 / 43卷 / 05期

关键词：

Liquid rate; Liquid rocket engine; Nonlinear; Sloshing; Tank; Wave surface breaking;

D O I：

10.13675/j.cnki.tjjs.200627

中图分类号：

学科分类号：

摘要：

During the flight of the launch vehicle, the propellant sloshing and wave surface breaking in the fuel tank impose a large disturbance force to the fuel tank. The disturbance will affect the flight stability if it is not effectively controlled. To study the effects of propellant sloshing on the tank structure, a nonlinear dynamic model of liquid sloshing in a cylinder tank is established. The proposed model combining Fluid Volume Method and Level Set Method is used to describe the breaking wave. Besides, the numerical calculation is carried out for analyzing the large sloshing of a 3D cylinder tank under various liquid rates. Then the changes of the free surface area, the force of the liquid on the wall, the sloshing velocity of the liquid and the center of liquid mass are obtained. Through the comparison of the calculation results under three liquid rates of 30%, 50% and 70%, it is found that the liquid in the launch vehicle tank changes from linear sloshing to nonlinear sloshing during the flight. Moreover, the liquid rate directly affects the sloshing intensity, the force on the wall, and the occurrence of nonlinear phenomena such as liquid wave breaking. The liquid rate of 50% is a relatively dangerous working condition. © 2022, Editorial Department of Journal of Propulsion Technology. All right reserved.

引用

页码：353 / 359

页数：6

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