摘要
研究欠驱动航天器姿态控制系统设计问题。首先给出了欠驱动航天器的姿态动力学方程和运动学方程。然后,基于系统模型的特点,采用分段解耦控制的思想,依次为动力学系统和运动学系统设计了渐近稳定的控制律,使航天器进入三轴稳定状态或自旋稳定状态。最后通过数值仿真验证了分段解耦控制方法的有效性。
This paper deals with the attitude control of an underactuated spacecraft.Firstly,the system dynamic and kinematic equations are given.Then,the properties of the model are analyzed in detail.Some asymptotically stabilized control laws are then designed for the two subsystems by means of piecewise decoupling.The control laws ultimately lead the spacecraft to 3-axis stabilized or spin stabilized.Simulating results validate the availability of the proposed control algorithm.
出处
《宇航学报》
EI
CAS
CSCD
北大核心
2007年第3期531-534,556,共5页
Journal of Astronautics
基金
国家自然科学基金(10372011)
关键词
欠驱动系统
姿态控制
分段解耦
Underactuated system
Attitude control
Piecewise decoupling
