基于IAMPF的航天器姿态确定算法

Spacecraft attitude determination algorithm based on IAMPF

对于航天器姿态确定系统中的滤波问题,提出一种基于改进辅助边缘粒子滤波(IAMPF)的姿态确定算法。该方法在辅助边缘粒子滤波(AMPF)的基础上引入快速高斯变换(FGT)方法,使得在辅助粒子滤波改进粒子滤波精度的基础上,使其效率也提高。将该方法用于陀螺/星敏感器组合定姿系统,并与PF、UKF及APF进行对比。仿真结果表明,在初始误差较大的情况下,该方法取得了较好的滤波效果。

Aiming at the filtering for spacecraft attitude determination system, an attitude determination algorithm based on im- proved auxiliary edge particle filter （IAMPF） was proposed. Fast Gaussian transform （FGT） was introduced into the method based on the auxiliary edge particle filter （AMPF） , because of which accuracy and efficiency of filtering were improved. This method was introduced into integrated attitude determination system based gyro / star sensor, and compared with PF, UKF and APF. The simu- lation results show that the method achieves better filtering effect in case of larger initial error.