摘要
本文给出了具有中心刚体和P个挠性附件的空间飞行器姿态动力学方程式,并用约束和非约束两种模态展开,得到时域求解的状态方程式和频域中的增广姿态角对控制力矩的逆传递函数阵。推导中考虑了挠性附件对中心刚体的相对运动。本文还给出了两种模态恒等式,其中之一可用来做控制系统分析时截断高阶方程式的截断准则。
The attitude dynamic equations of spacecraft with a central rigid body and P flexible appendages are derived. Expanding these equations in series by both unconstrained and constrained mode shape functions the state equations in time domain and the inverse transfer function matrix, defined as the relation of augmented attitude angle matrix to control forces or moments in frequency domain are obtained. The relative motion of flexible appendages to central rigid body are considered, too, in derivation. This paper gives also two modal identities, one of which can be regarded as the criteria for trunction of higher order equations obtained when the attitude control system is being analyzed.
出处
《宇航学报》
EI
CAS
CSCD
北大核心
1989年第4期87-95,共9页
Journal of Astronautics
基金
自然科学基金"技85016"支持
关键词
挠性附件
卫星
姿态控制
截断
Dynamics of spacecraft, Flexible appendage, Attitude control, Truncation.
