大型充液卫星贮箱‘正反装’情况下的特性研究

本文详细地描述了带有中心承力式双元大贮箱的大型充液卫星的液体晃动摆与卫星耦合的动力学模型;用传递函数零极点法定性地分析了控制系统的稳定性,按照实际工程设计方法考虑了晃动模型参数允差,具体地比较了贮箱‘正反装’情况下控制系统最坏允差组合时的稳定裕度和动态性能,研究了贮箱‘正反装’情况下的星箭匹配问题。研究结果表明,在控制系统稳定性方面,‘正装’、‘反装’不相上下,在星箭匹配和控制系统动态性能方面,‘正装’优于‘反装’,从而证明了选择‘正装’的合理性和必要性。

Character Research of the Large Satellite with Two Big Liquid-Propellant Tanks in Normal or Upside-down Cases

This paper deals with the dynamic model of the large satellite coupling with the liq- uid sloshing pendulums of the bi-propellant tanks which are center forcing structure. A qualita- tive analysis of the stability of the control system using the trans fer function zeros--poles meth- od is given. According to the actual engineering design method, the tolerances of the parameters of the liquid sloshing model are taken into account. The stability margins of the worst--case combination of the sloshing parameter tolerances and the transition per formances are compared quantitatively when the propellant tanks are in normal case (the upper tank is fil- led with MMH, the lower tank is filled with NTO) or in upside--down case. The matching problem of the satellite--launcher under the normal case or the upsidedown case are investi- gated. The conclusions of the research are that the stabilities of the control system almost the same under the two cases, the satellite--launcher matching characters and transition perform- ances of the normal case are better than these of the upside--down case. So that it is reasonable and necessary to choose the normal case as the basis of design.