Calculating global navigation satellite system satellite velocities and accelerations by utilizing the orbit fitting and orbit integration methods
The high-precision satellite velocities and accelerations calculated by the Global Navigation Satellite System (GNSS) are essential for tasks such as airborne gravity data processing. Users generally interpolate satellite positions in the precise ephemeris to calculate satellite velocity and acceler...
| Main Authors: | , , , , |
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| Other Authors: | |
| Format: | Journal Article |
| Language: | English |
| Published: |
2024
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| Subjects: | |
| Online Access: | https://hdl.handle.net/10356/181584 |
| _version_ | 1826116307845644288 |
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| author | Song, Chuanfeng Geng, Shilong Chen, Liang An, Xiangdong Ma, Hongyang |
| author2 | School of Electrical and Electronic Engineering |
| author_facet | School of Electrical and Electronic Engineering Song, Chuanfeng Geng, Shilong Chen, Liang An, Xiangdong Ma, Hongyang |
| author_sort | Song, Chuanfeng |
| collection | NTU |
| description | The high-precision satellite velocities and accelerations calculated by the Global Navigation Satellite System (GNSS) are essential for tasks such as airborne gravity data processing. Users generally interpolate satellite positions in the precise ephemeris to calculate satellite velocity and acceleration. However, due to the edge effect, the accuracy of the interpolation is relatively low near day boundaries. In this study, a method for calculating GNSS satellite velocity and acceleration based on orbit fitting and orbit integration was proposed, and the high-precision transformation relationship between satellite velocity and acceleration in the Earth-Centered Inertial (ECI) coordinate system and the Earth-Centered, Earth-Fixed (ECEF) coordinate system was derived. The experimental results show that the satellite velocity accuracy is 1.5 × 10−6 m/s and the acceleration accuracy is 1.0 × 10−8 m/s2 according to the proposed method. Thus, the proposed method improves the accuracy of calculating satellite velocity and acceleration near day boundaries, and helps GNSS users to obtain satellite velocity and acceleration information with consistent precision throughout the day. |
| first_indexed | 2025-03-09T11:37:01Z |
| format | Journal Article |
| id | ntu-10356/181584 |
| institution | Nanyang Technological University |
| language | English |
| last_indexed | 2025-03-09T11:37:01Z |
| publishDate | 2024 |
| record_format | dspace |
| spelling | ntu-10356/1815842024-12-13T15:42:17Z Calculating global navigation satellite system satellite velocities and accelerations by utilizing the orbit fitting and orbit integration methods Song, Chuanfeng Geng, Shilong Chen, Liang An, Xiangdong Ma, Hongyang School of Electrical and Electronic Engineering Engineering Orbit fitting Orbit integration The high-precision satellite velocities and accelerations calculated by the Global Navigation Satellite System (GNSS) are essential for tasks such as airborne gravity data processing. Users generally interpolate satellite positions in the precise ephemeris to calculate satellite velocity and acceleration. However, due to the edge effect, the accuracy of the interpolation is relatively low near day boundaries. In this study, a method for calculating GNSS satellite velocity and acceleration based on orbit fitting and orbit integration was proposed, and the high-precision transformation relationship between satellite velocity and acceleration in the Earth-Centered Inertial (ECI) coordinate system and the Earth-Centered, Earth-Fixed (ECEF) coordinate system was derived. The experimental results show that the satellite velocity accuracy is 1.5 × 10−6 m/s and the acceleration accuracy is 1.0 × 10−8 m/s2 according to the proposed method. Thus, the proposed method improves the accuracy of calculating satellite velocity and acceleration near day boundaries, and helps GNSS users to obtain satellite velocity and acceleration information with consistent precision throughout the day. Published version This study is supported by the Young Scientists Fund of the National Natural Science Foundation of China (No.42304099), the Liaoning Provincial Department of Education Basic Research Project (JYTZD2023071), the Key Laboratory of Smart Earth (NO. KF2023YB01-03), the Young Elite Scientists Sponsorship Program by CAST (YESS20200308), and the Beijing Nova Program (Z211100002121068). 2024-12-10T02:30:21Z 2024-12-10T02:30:21Z 2024 Journal Article Song, C., Geng, S., Chen, L., An, X. & Ma, H. (2024). Calculating global navigation satellite system satellite velocities and accelerations by utilizing the orbit fitting and orbit integration methods. Remote Sensing, 16(13), 16132366-. https://dx.doi.org/10.3390/rs16132366 2072-4292 https://hdl.handle.net/10356/181584 10.3390/rs16132366 2-s2.0-85198398163 13 16 16132366 en Remote Sensing © 2024 by the authors. Licensee MDPI, Basel, Switzerland. This article is an open access article distributed under the terms and conditions of the Creative Commons Attribution (CC BY) license (https:// creativecommons.org/licenses/by/ 4.0/). application/pdf |
| spellingShingle | Engineering Orbit fitting Orbit integration Song, Chuanfeng Geng, Shilong Chen, Liang An, Xiangdong Ma, Hongyang Calculating global navigation satellite system satellite velocities and accelerations by utilizing the orbit fitting and orbit integration methods |
| title | Calculating global navigation satellite system satellite velocities and accelerations by utilizing the orbit fitting and orbit integration methods |
| title_full | Calculating global navigation satellite system satellite velocities and accelerations by utilizing the orbit fitting and orbit integration methods |
| title_fullStr | Calculating global navigation satellite system satellite velocities and accelerations by utilizing the orbit fitting and orbit integration methods |
| title_full_unstemmed | Calculating global navigation satellite system satellite velocities and accelerations by utilizing the orbit fitting and orbit integration methods |
| title_short | Calculating global navigation satellite system satellite velocities and accelerations by utilizing the orbit fitting and orbit integration methods |
| title_sort | calculating global navigation satellite system satellite velocities and accelerations by utilizing the orbit fitting and orbit integration methods |
| topic | Engineering Orbit fitting Orbit integration |
| url | https://hdl.handle.net/10356/181584 |
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