变轨发动机工作态主动式自旋稳定姿态控制  

Active attitude control for a spin-stablized spacecraft while the orbit transform motor is working

作　　者：李雯[1] 肖凯[1] 

机构地区：[1]国防科技大学航天与材料工程学院宇航科学与工程系,长沙410073

出　　处：《宇航学报》2004年第2期231-234,共4页Journal of Astronautics

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.

关 键 词：航天器 变轨发动机 姿态控制 自旋稳定控制 

分 类 号：TJ765[兵器科学与技术—武器系统与运用工程]