摘要
首先通过对航天器变轨控制的分析,提出了"通过消章消偏综合控制实现自旋稳定姿态控制"的主动式自旋稳定姿态控制方法;随后,分别研究了变轨发动机工作态的消章控制和消偏控制的特点和相应方法;最后,设计并实现了"带消偏约束的消章控制法"。应用该方法对某细长型航天器的变轨发动机工作态进行控制,仿真结果表明,姿态控制的精度较高。
In this paper,firstly,controling an orbit changing spacecraft was analyzed,an active attitude control method -'reduce nutation and deflection synthetically to implement attitude control for a spin-stablized spacecraft' was suggested.Secondly,the characteristics and methods of reducing nutation control and reducing deflection control while the orbit transform motor was working were studied respectively.Finally,'reducing nutation control method with the restriction of reducing deflection' was designed.This method was applied to control some slender spacecraft while the orbit transform motor was working,the simulation result shows that the precision of the attitude control is quite high.
出处
《宇航学报》
EI
CAS
CSCD
北大核心
2004年第2期231-234,共4页
Journal of Astronautics
关键词
航天器
变轨发动机
姿态控制
自旋稳定控制
Spacecraft
Orbit transform motor
Attitude control
Spin-stablized control