摘要
本文研究了带挠性附件双自旋卫星的姿态稳定性问题。假定挠性双自旋卫星由无内部活动部件的半刚性平台、半刚性转子以及固连于平台的挠性附件构成,选择姿态角和模态坐标表示的相对能量函数为Liapunov 函数,建立了挠性双自旋卫星姿态稳定性判据。
The problem of attitude stability of dual spin satellites with flexible appendages is studied inthis paper.The model of the flexible dual spin satellite consists of a semirigid platform with asemirigid axisymmetrie rotor and n flexible appendages attached to it.The relative energy func-tion of the system is selected as a Liapunov function in terms of the attitude angles and mode co-ordinates,and the attitude stability criteria is obtained by using the Liapunov stability theorem.
出处
《国防科技大学学报》
EI
CAS
CSCD
北大核心
1991年第3期1-9,共9页
Journal of National University of Defense Technology
关键词
双自旋卫星
LIAPUNOV
稳定性
卫星
flexible dual spin satellites
Liapunov function
attitude stability
