一种SGCMG系统奇异逃离方法  

A Singularity Escape Method for SGCMG System

作　　者：刘德庆 吴敬玉 操宏磊 

机构地区：[1]上海航天控制技术研究所,上海201109 [2]上海市空间智能控制技术重点实验室,上海201109

出　　处：《宇航学报》2016年第8期1001-1005,共5页Journal of Astronautics

摘　　要：单框架控制力矩陀螺(SGCMG)系统进入奇异后无法提供准确的三轴指令力矩,通过奇异机理分析,设计了一种奇异逃离方案。首先构造新的动态坐标系,在系统进入奇异后,将控制坐标系切换到新的坐标系下,在新的坐标系上放弃一个维度的控制,将系统考虑为平面内的SGCMG冗余控制系统,然后在平面内采用二维零运动使得系统快速逃离奇异状态,当SGCMG系统逃离奇异状态后,再重新接入三维度的控制。仿真结果表明,提出的方法具有很好的奇异逃避效果。Single gimbal control moment gyros（ SGCMG） system cannot afford accurate three axis torque in singular states. A singularity escape method is designed based on the analysis of singularity principle. Firstly,a new dynamic coordinate system is created and switched as the steering reference coordinate system. Secondly,one of the control dimensions is abandoned when the SGCMG system moves into the singular state and the system is considered as a redundant SGCMG control system within a plane. Thirdly,a null motion in the two dimensional space is provided so that the SGCMG can move out of the singular state quickly. Finally,the three dimensional steering law needs to be switched on after the SGCMG system escapes from the singular state. The method＇s impressive performance on singularity escape is demonstrated by the simulation results.

关 键 词：航天器 单框架控制力矩陀螺(SGCMG) 姿态控制 奇异逃离 

分 类 号：V448.22[航空宇航科学与技术—飞行器设计]