摘要
基于液体大幅晃动等效力学模型研究充液航天器动力学与控制问题。首先,发展并完善了模拟液体大幅晃动的运动脉动球模型(MPBM),结合已有的液体大幅晃动运动规律和分析结论对MPBM的法向力的计算方法进行了改进;通过数值仿真结果与已有试验结果的对比证明了以上改进工作的有效性。然后,基于MPBM建立了携带多个充液储箱的航天器动力学模型,针对携带四个储箱的充液航天器进行姿态机动控制研究。研究结果表明,四个充液储箱的三种可能的空间布局对航天器姿态机动过程中的角速度、液体晃动力矩和控制力矩将产生不同的影响;此外,还研究了液体大幅晃动等效力学模型中液体晃动阻尼因素对航天器姿态机动控制的影响。
The dynamics and control for the liquid filled spacecraft are explored based on the equivalent mechanical model of large amplitude liquid slosh. Firstly,a mechanical equivalent model for large amplitude slosh,the moving pulsating ball model（ MPBM）,is improved by modifying the calculation of the normal force of the MPBM according to the motion law and analytical results for the large amplitude liquid slosh. The improvements on MPBM are validated with the comparisons between the previous published experimental results and the presented numerical simulation. Subsequently,the kinetic equations are built for the liquid filled spacecraft with multiple fuel tanks by using this improved model. The attitude dynamics and control of the liquid filled spacecraft with four liquid filled tanks is investigated. Through the numerical simulation results,it is found that the angular rate,liquid sloshing torque and control torque can be influenced in different ways by the assumed three different tank arrangements. Moreover,the influence of liquid sloshing damping on the attitude control strategy is also studied.
出处
《宇航学报》
EI
CAS
CSCD
北大核心
2016年第6期631-638,共8页
Journal of Astronautics
基金
国家自然科学基金(11472041
11532002)
高等学校博士点专项科研基金(20131101110002)
关键词
运动脉动球模型(MPBM)
充液航天器
液体大幅晃动
多储箱
姿态控制
Moving pulsating ball model（MPBM）
Liquid filled spacecraft
Large amplitude liquid slosh
Multiple tanks
Attitude control
