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.