TY - JOUR
T1 - Comparison on EKF and UKF for geomagnetic attitude estimation of LEO satellites
AU - Yang, Bin
AU - Xu, Guanghan
AU - Jin, Jin
AU - Zhou, You
PY - 2012/12
Y1 - 2012/12
N2 - A low Earth orbit (LEO) satellite can be stabilized in 3-axis by corporately using a magnetometer, reaction wheels and 3-axis magnetorquer rods. It is challenging to determinate an appropriate attitude for LEO. To address this challenge, the algorithms of extended Kalman filter (EKF) and unscented Kalman filter (UKF) were compared and a solution was proposed by exploring the influence of the geomagnetic model error, the magnetic measurement error and the remanence on the performance of attitude determination. In addition, the calculation of mean and covariance quaternion was derived. The EKF and UKF were introduced to attitude determination, and the factors which have influence on the algorithm performance were discussed. Two algorithms were compared on estimation accuracy, convergence time and computation complexity. With the accuracy requirements and the hardware limitations, the EKF algorithm was finally chosen for the attitude determination. Simulation results show that the earth pointing accuracy of the proposed solution can reach 1° with the stability of 0.1(°)/s.
AB - A low Earth orbit (LEO) satellite can be stabilized in 3-axis by corporately using a magnetometer, reaction wheels and 3-axis magnetorquer rods. It is challenging to determinate an appropriate attitude for LEO. To address this challenge, the algorithms of extended Kalman filter (EKF) and unscented Kalman filter (UKF) were compared and a solution was proposed by exploring the influence of the geomagnetic model error, the magnetic measurement error and the remanence on the performance of attitude determination. In addition, the calculation of mean and covariance quaternion was derived. The EKF and UKF were introduced to attitude determination, and the factors which have influence on the algorithm performance were discussed. Two algorithms were compared on estimation accuracy, convergence time and computation complexity. With the accuracy requirements and the hardware limitations, the EKF algorithm was finally chosen for the attitude determination. Simulation results show that the earth pointing accuracy of the proposed solution can reach 1° with the stability of 0.1(°)/s.
KW - Attitude determination
KW - Extended Kalman filter
KW - Geomagnetic measurement
KW - Low Earth orbit satellite
KW - Unscented Kalman filter
UR - https://www.scopus.com/pages/publications/84872820180
U2 - 10.3780/j.issn.1000-758X.2012.06.004
DO - 10.3780/j.issn.1000-758X.2012.06.004
M3 - 文章
AN - SCOPUS:84872820180
SN - 1000-758X
VL - 32
SP - 23-30+38
JO - Zhongguo Kongjian Kexue Jishu/Chinese Space Science and Technology
JF - Zhongguo Kongjian Kexue Jishu/Chinese Space Science and Technology
IS - 6
ER -