摘要
在热备份的余度配置陀螺与星敏感器的组合定姿中,典型的三轴正交陀螺与星敏感器姿态确定算法受到限制;现以某微小卫星姿控系统为对象,设计了热备份的四陀螺系统与星敏感器组合定姿方法;数据处理时,利用最小二乘法将四陀螺测量系统构建为一个虚拟三轴正交陀螺,再将虚拟陀螺与星敏感器组成卡尔曼滤波器;该方法和典型的三正交陀螺与星敏感器组合定姿结构相同,实现简单,且在一陀螺发生故障时,能在不改变滤波器结构的情况下实现对故障陀螺的屏蔽;仿真验证了该方法的有效性。
This paper analyses a method using gyros and star sensor to obtain satellite attitude for a specific satellite. To get high reliability, this system uses four gyros. Using least square to change 4 gyros system to 3 virtual gyros system, then use extend kalman filter （EKF） to fuse the data of virtual gyros system and star sensor. The simulation result shows that this method can give us high attitude accuracy. It still can get high accuracy when one of them degrades.
出处
《计算机测量与控制》
CSCD
2008年第5期634-636,共3页
Computer Measurement &Control
关键词
卫星姿态
扩展卡尔曼滤波
最小二乘法
冗余陀螺
虚拟陀螺
satellite attitude
extended kalman filter
least square
redundant gyros system
virtual gyros
