TY - GEN
T1 - Spacecraft Attitude Determination Based on Combination of FLAE Algorithm and UKF
AU - Zhu, Yizhuo
AU - Zhang, Hui Juan
AU - Ji, Miaoxin
AU - Mi, Hanguang
AU - Yu, Yuan Jin
N1 - Publisher Copyright:
© The Author(s), under exclusive license to Springer Nature Singapore Pte Ltd. 2025.
PY - 2025
Y1 - 2025
N2 - An attitude estimation algorithm, which combines Unscented Kalman Filter (UKF) and Fast Linear Attitude Estimator (FLAE), is proposed for integrated inertial/starlight attitude determination systems based on gyros and star trackers. The attitude quaternion is firstly determined by the FLAE algorithm which uses the measurement signal of star trackers, and then the determined attitude quaternion is served as the state variable for UKF. Furthermore, the gyros drift is estimated by UKF, and then the system errors are compensated. The attitude error of FLAE-UKF is approximately ± 1″, with no significant difference compared to the UKF. The gyro drift estimates of both the FLAE-UKF and the UKF reach 0.5°/h within 15–30 s. This indicates that the FLAE-UKF maintains the same accuracy as the UKF in both attitude angle estimation and gyro drift estimation. Under different sampling times, the computational cost of the FLAE-UKF is decreased by at least 1/20 compared to the UKF. This indicates that the FLAE-UKF achieves reduced computational cost while maintaining the same accuracy as the UKF.
AB - An attitude estimation algorithm, which combines Unscented Kalman Filter (UKF) and Fast Linear Attitude Estimator (FLAE), is proposed for integrated inertial/starlight attitude determination systems based on gyros and star trackers. The attitude quaternion is firstly determined by the FLAE algorithm which uses the measurement signal of star trackers, and then the determined attitude quaternion is served as the state variable for UKF. Furthermore, the gyros drift is estimated by UKF, and then the system errors are compensated. The attitude error of FLAE-UKF is approximately ± 1″, with no significant difference compared to the UKF. The gyro drift estimates of both the FLAE-UKF and the UKF reach 0.5°/h within 15–30 s. This indicates that the FLAE-UKF maintains the same accuracy as the UKF in both attitude angle estimation and gyro drift estimation. Under different sampling times, the computational cost of the FLAE-UKF is decreased by at least 1/20 compared to the UKF. This indicates that the FLAE-UKF achieves reduced computational cost while maintaining the same accuracy as the UKF.
KW - Attitude determination
KW - Fast Linear Attitude Estimator
KW - Gyros
KW - Star tracker
KW - Unscented Kalman filter
UR - https://www.scopus.com/pages/publications/105000346682
U2 - 10.1007/978-981-96-2260-3_58
DO - 10.1007/978-981-96-2260-3_58
M3 - Conference contribution
AN - SCOPUS:105000346682
SN - 9789819622597
T3 - Lecture Notes in Electrical Engineering
SP - 594
EP - 603
BT - Advances in Guidance, Navigation and Control - Proceedings of 2024 International Conference on Guidance, Navigation and Control Volume 16
A2 - Yan, Liang
A2 - Duan, Haibin
A2 - Deng, Yimin
PB - Springer Science and Business Media Deutschland GmbH
T2 - International Conference on Guidance, Navigation and Control, ICGNC 2024
Y2 - 9 August 2024 through 11 August 2024
ER -