摘要
充液航天器内部液体晃动及其对控制系统的影响,是当前国内外航天高科技研究的重要课题,也是一个比较复杂的问题。本文首先由力学变分原理导出充液系统的状态方程,其次分析了充液系统的稳定性,简述了在微重条件下充液航天器内部液体晃动的动力学特性。
Liquid sloshing in spacecraft with its effect to controlling system is a important question and it is also a complicate question.In this paper the state equation of filling liquid system is given, the stability of filling liquid system is analysed and the dynamic characteristics of liquid slosh in spacecraft under lowgravity is given.
出处
《安庆师范学院学报（自然科学版）》
2002年第4期20-22,51,共4页
Journal of Anqing Teachers College(Natural Science Edition)
基金
安徽省重点科研项目(00021090)
