TY - GEN
T1 - Non-Cooperative LEO Satellite Orbit Determination Using Pseudorange Based on Single Station
AU - Deng, Ruofan
AU - Qin, Honglei
AU - Shi, Guangting
N1 - Publisher Copyright:
© 2023 IEEE.
PY - 2023
Y1 - 2023
N2 - Non-cooperative low-Earth-orbit (LEO) satellites have promising applications, the prerequisite of obtaining accurate orbits. In this paper, we propose a non-cooperative LEO satellite orbit determination method using pseudorange with only a single station, which is less affected by interference, occlusion, and weather changes, has low hardware cost, and is free from space-time reference unification and information transmission between receivers. The single station extracts pseudorange observations from signals of opportunity (SOPs), and then the observations are processed by a batch least squares (LS) filter to estimate orbit. Finally, the feasibility of the proposed method is verified by the real experiment, taking Iridium as an example. According to the result, the determined orbit has accuracy comparable to Two-Line Elements (TLE), and the predicted errors of elevation azimuth and Doppler frequency deviation after 3 days are within 0.15°, 2.5°, and 120 Hz, respectively.
AB - Non-cooperative low-Earth-orbit (LEO) satellites have promising applications, the prerequisite of obtaining accurate orbits. In this paper, we propose a non-cooperative LEO satellite orbit determination method using pseudorange with only a single station, which is less affected by interference, occlusion, and weather changes, has low hardware cost, and is free from space-time reference unification and information transmission between receivers. The single station extracts pseudorange observations from signals of opportunity (SOPs), and then the observations are processed by a batch least squares (LS) filter to estimate orbit. Finally, the feasibility of the proposed method is verified by the real experiment, taking Iridium as an example. According to the result, the determined orbit has accuracy comparable to Two-Line Elements (TLE), and the predicted errors of elevation azimuth and Doppler frequency deviation after 3 days are within 0.15°, 2.5°, and 120 Hz, respectively.
KW - Non-cooperative LEO satellite
KW - orbit determination
KW - pseudorange
UR - https://www.scopus.com/pages/publications/85170030044
U2 - 10.1109/EEI59236.2023.10212485
DO - 10.1109/EEI59236.2023.10212485
M3 - 会议稿件
AN - SCOPUS:85170030044
T3 - 2023 5th International Conference on Electronic Engineering and Informatics, EEI 2023
SP - 463
EP - 467
BT - 2023 5th International Conference on Electronic Engineering and Informatics, EEI 2023
PB - Institute of Electrical and Electronics Engineers Inc.
T2 - 5th International Conference on Electronic Engineering and Informatics, EEI 2023
Y2 - 30 June 2023 through 2 July 2023
ER -