火箭三级无动力飞行段晃动的一种建模方法  

A Modeling Method for Propellant-Sloshing of Launch Vehicle in Third Stage Flight without Power

作　　者：修观 李鑫 

机构地区：[1]上海宇航系统工程研究所,上海201109

出　　处：《上海航天》2015年第1期22-24,29,共4页Aerospace Shanghai

摘　　要：对某运载火箭三级无动力飞行段晃动不稳定和姿态超差现象进行了分析。采用等效弹簧-质量晃动模型,基于牛顿-欧拉法建立了一种新的液体晃动方程,表明液体晃动与重力无关。对基于包含新的液体晃动方程的姿态动力学模型设计、仿真和飞行试验的结果表明:该晃动方程正确,可解决工程应用中的晃动不稳定和姿态超差问题。The propellant sloshing un-stability and large attitude deviation of some launch vehicle in its third stage flight without power were analyzed in this paper.The equal mass-spring model was adopted to describe fuelslosh.A new sloshing equation was established based on Newton-Euler method.It was proved that the fuel-slosh was not related to the gravity.The attitude dynamic model including the new sloshing equation was used to design the control system of launch vehicle.The numerical simulation and flight test results showed that the new sloshing equation was correct,and the propellant sloshing un-stability and large attitude deviation problems were resolved in engineering.

关 键 词：运载火箭 推进剂晃动 晃动方程 稳定性 姿态 

分 类 号：V412.1[航空宇航科学与技术—航空宇航推进理论与工程]