液体火箭冷弹射系统推进剂晃动研究  

Research on Propellant Sloshing of Liquid Rocket Cold Launch System

作　　者：魏冬冬[1] 姜毅[1] 赵良玉[1] 李玉龙 WEI Dongdong;JIANG Yi;ZHAO Liangyu;LI Yulong(School of Aerospace Engineering,Beijing Institute of Technology,Beijing 100081,China;No.96901 Unit,Beijing 100094,China)

机构地区：[1]北京理工大学宇航学院,北京100081 [2]96901部队,北京100094

出　　处：《弹箭与制导学报》2021年第3期34-38,共5页Journal of Projectiles,Rockets,Missiles and Guidance

摘　　要：为了研究液体推进剂晃动对火箭发射精度和发射安全性的影响,利用流-固耦合技术对液体火箭冷弹射系统进行建模仿真,将不考虑推进剂晃动的多体弹射系统与考虑晃动的流-固耦合弹射系统进行对比,通过冷弹射子模型与液体推进剂子模型之间的数据交互,研究推进剂晃动对火箭发射过程的扰动情况。结果表明,推进剂的晃动会对火箭产生较大扰动力和力矩,延长离轨时间,增大离轨角速度。In order to study the impact of liquid propellant sloshing on rocket launch accuracy and launch safety,the fluid-structure coupling technology is used to model and simulate the liquid rocket cold ejection system.Through the data interaction between the cold launch sub-model and the liquid propellant sub-model,the disturbance of the propellant sloshing to the rocket launching process is studied by comparing the launch system without considering the propellant sloshing with the fluid-structure coupling launch system which considers the propellant sloshing.The results show that the sloshing of the propellant can cause a greater disturbance force and moment of the rocket,prolong the off-orbit time,and increase the off-orbit angular velocity.

关 键 词：流-固耦合 移动粒子半隐式法 液体晃动 

分 类 号：V434[航空宇航科学与技术—航空宇航推进理论与工程]