Influence of propellant filling ratio for liquid rocket cold ejection on rocket launch accuracy

被引：0
作者：
Wang J. [1 ]
Jiang Y. [1 ]
Yang C. [2 ]
Wei D. [2 ]
机构：
[1] Beijing Institute of Technology, School of Aerospace Engineering, Beijing
[2] Tactical Weapons Division, China Academy of Launch Vehicle Technology, Beijing
来源：
Zhendong yu Chongji/Journal of Vibration and Shock | 2023年 / 42卷 / 06期
关键词：
fluid-structure coupling; liquid filling ratio; liquid rocket; propellant sloshing;
D O I：
10.13465/j.cnki.jvs.2023.06.038
中图分类号：
学科分类号：
摘要：
In order to study the effects of liquid propellant sloshing at different liquid filling ratio on rocket launch accuracy under cold ejection load, the liquid rocket under cold ejection was studied. The dynamic response of propellant sloshing was studied by the fluid-solid coupling technique based on MPS ( moving particle semi-implicit) method. The interference on rocket tank and influence on initial disturbance of the rocket and the mechanical characteristics of the adaptor at different propellant liquid filling ratio were investigated. The results show that the larger the liquid filling ratio is，the greater the force of liquid propellant on a single tank is ； in a certain range，with the increase of the filling ratio， the propellant sloshing makes the off-orbit pitch and yaw angular velocity of the rocket increase first and then decrease ； when the liquid filling ratio is 80%，the initial disturbance situation of the rocket and the force state of the adaptor are worse. Propellant sloshing can not be ignored in the dynamics study of liquid rocket cold ejection. © 2023 Chinese Vibration Engineering Society. All rights reserved.
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页码：313 / 320
页数：7
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