This article deals with torque allocation for redundant flywheel configurations in a spacecraft attitude control system.
主要研究了航天器姿控系统中冗余飞轮构型的力矩分配问题。
The relation among parameters is derived and the stability of single axis flexible spacecraft attitude control system is studied.
推导系统参数间的关系式，分析挠性空间飞行器主轴姿态控制系统稳定性问题。
In this paper, the basic theory of the inverse system method is introduced, and is used in the design of a spacecraft attitude control system.
本文首先介绍了逆系统方法的基本思想，然后将其用于航天器非线性姿态控制系统的设计中。
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