Abstract
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.
| Original language | English |
|---|---|
| Pages (from-to) | 23-30+38 |
| Journal | Zhongguo Kongjian Kexue Jishu/Chinese Space Science and Technology |
| Volume | 32 |
| Issue number | 6 |
| DOIs | |
| State | Published - Dec 2012 |
Keywords
- Attitude determination
- Extended Kalman filter
- Geomagnetic measurement
- Low Earth orbit satellite
- Unscented Kalman filter
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