摘要
以中心刚体带柔性附件的航天器为对象，研究了姿态控制时中心体的转动惯量与附件振动衰减速率之间的关系。以此为基础提出一种附件振动抑制和附件指向控制的方法——根部控制法。结果表明，此方法可明显抑制附件振动，并对姿态控制的影响很小。
Deals with the vibration control of spacecraft with flexible appendages.The relationships between the moment of inertia of spacecraft and vibration damping ratio of appendages in attitude control are analyzed.An approach for pointing control and vibration suppession of appendages is presented based on the above analysis.The results show that the vibration of appendages is suppressed significantly,and the attitude control is slightly affected.
出处
《振动工程学报》
EI
CSCD
1997年第1期92-95,共4页
Journal of Vibration Engineering
基金
国家自然科学基金
关键词
柔性结构
航天器
柔性附件
振动控制
姿态控制
flexible structures
spacecrft
flexible
appendages
vibration control
attitude control
