[논문]Validation of Geostationary Earth Orbit Satellite Ephemeris Generated from Satellite Laser Ranging

Oh, Hyungjik; Park, Eunseo; Lim, Hyung-Chul; Lee, Sang-Ryool; Choi, Jae-Dong; Park, Chandeok

doi:10.5140/jass.2018.35.4.227

Validation of Geostationary Earth Orbit Satellite Ephemeris Generated from Satellite Laser Ranging 원문보기

Journal of astronomy and space sciences, v.35 no.4, 2018년, pp.227 - 233

Oh, Hyungjik (Department of Astronomy, Yonsei University) , Park, Eunseo (Korea Astronomy and Space Science Institute) , Lim, Hyung-Chul (Korea Astronomy and Space Science Institute) , Lee, Sang-Ryool (Korea Aerospace Research Institute) , Choi, Jae-Dong (Korea Aerospace Research Institute) , Park, Chandeok (Department of Astronomy, Yonsei University)

Abstract ▼ AI-Helper

This study presents the generation and accuracy assessment of predicted orbital ephemeris based on satellite laser ranging (SLR) for geostationary Earth orbit (GEO) satellites. Two GEO satellites are considered: GEO-Korea Multi-Purpose Satellite (KOMPSAT)-2B (GK-2B) for simulational validation and Compass-G1 for real-world quality assessment. SLR-based orbit determination (OD) is proactively performed to generate orbital ephemeris. The length and the gap of the predicted orbital ephemeris were set by considering the consolidated prediction format (CPF). The resultant predicted ephemeris of GK-2B is directly compared with a pre-specified true orbit to show 17.461 m and 23.978 m, in 3D root-mean-square (RMS) position error and maximum position error for one day, respectively. The predicted ephemeris of Compass-G1 is overlapped with the Global Navigation Satellite System (GNSS) final orbit from the GeoForschungsZentrum (GFZ) analysis center (AC) to yield 36.760 m in 3D RMS position differences. It is also compared with the CPF orbit from the International Laser Ranging Service (ILRS) to present 109.888 m in 3D RMS position differences. These results imply that SLR-based orbital ephemeris can be an alternative candidate for improving the accuracy of commonly used radar-based orbital ephemeris for GEO satellites.

주제어

표/그림 (12)

그림 Fig. 1. GK-2B GEO Satellite (Image Courtesy of KARI).
그림 Fig. 2. Geochang SLR station at Mt. Gamak.
그림 Fig. 3. Orbital ephemeris generation and comparison process.
그림 Fig. 4. Precise orbital ephemeris errors of GK-2B (1 day).
그림 Fig. 5. Precise orbital ephemeris errors of GK-2B (1 week).
표 Table 1. Dynamic Model Parameters for ephemeris generation of GEO satellite
표 Table 2. Precise orbital ephemeris errors of GK-2B (1 day)
표 Table 3. Precise orbital ephemeris errors of GK-2B (1 week)
그림 Fig. 6. Differences between SLR-based ephemeris and GFZ final orbit of Compass-G1 (1 week).
그림 Fig. 7. Differences between SLR-based ephemeris and ILRS CPF of Compass-G1.
표 Table 4. Diferences between SLR-based ephemeris and GFZ Final orbit of Compass-G1 (1 week)
표 Table 5. Diferences between SLR-based Ephemeris and ILRS CPF of Compass-G1

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문제 정의

LRA will be mounted on the satellite bus to obtain SLR data. The primary objective of SLR is to maintain the precise OD while validating the SLR technology for future domestic satellite missions. Specific satellite parameter information for GK-2B are found in Oh et al.

제안 방법

In an attempt to justify the simulational validation of GK-2B ephemeris, verification of the OD and ephemeris generation strategy in “real world” conditions was carried out.
According to the simulation results, the accuracy of SLR-based predicted ephemeris for GK-2B remains precise for a day. OD errors were found to be less than those of the predicted ephemeris; while the OD errors were calculated for the period of one week, prediction is performed only for one day followed by the OD process. This implies that the SLR-based orbit prediction maintains its accuracy for a one day period.
A higher accuracy of orbital ephemeris would widen the applicability of GEO missions. To determine the feasibility of SLR-based precise orbital ephemeris of GK-2B, this study generated orbital ephemeris using an SLR-based OD solution and analyzed its accuracy.
(2018). Two scenarios were constructed to analyze the effect of the number of SLR measurements on the OD accuracy. For a one-week arc, the sparse case collects 9 NPs every day from the Geochang SLR station, while the dense case collects 13 NPs.

대상 데이터

It was then externally compared with two different orbital sources: the final orbit from the International Global Navigation Satellite System (GNSS) service (IGS) and the ILRS CPF orbit. GeoForschungsZentrum (GFZ), one of the IGS analysis centers (AC), was selected as the final orbit provider. The accuracy of the GFZ final orbit was qualified by direct comparison with the ephemeris made by Wuhan AC to yield errors of about 3 m (Deng et al.
The OD of Compass-G1 was performed with the same strategy as that used for GK-2B. The SLR data from the Changchun Chinese SLR station was applied from October 21 to 24, 2017. The 3D errors of OD of Compass-G1 were 31.

이론/모형

The reference orbit is proactively generated by the true simulated orbit of GK-2B and compared with the predicted ephemeris. The predicted ephemeris is generated by considering the consolidated prediction format (CPF) of the International Laser Ranging Service (ILRS). It is commonly used for formatting SLR-based precise orbital ephemeris and provides satellite orbital state information in tables of X, Y, and Z positions.

성능/효과

These differences are more significant than the error of the GK-2B simulation, as it should be due to the unmodeled dynamic models and measurement errors that exist in the real world. Despite the increasing differences as time elapses, these results indicate that the predicted orbital ephemeris based on the OD with SLR measurements maintained decimeter level accuracy for a one-day period.
In this paper, we consider the dense case with 91 NPs in one week. The OD errors of GK-2B were evaluated by directly differencing the determined orbit and the simulated (true) reference orbit for one week-length period to yield 43.46 m and 24.01 m as 3D root-mean-square (RMS) values for the sparse and the dense case, respectively.
(2008) analyzed the errors of TLE by categorizing the orbital characteristics of space objects. The orbital errors of TLE for GEO satellites in a one-day period were about 500 m in the along-track and cross-track directions and were less than 100 m in the radial direction. This may become aggravated when satellites are in a certain maneuver duration, which can result in a large error in the orbit propagation step.
The generated predicted orbital ephemeris of the Compass-G1 was externally compared with the final orbit based on GNSS signals and the CPF from the ILRS. While the results showed differences of hundreds of meters compared with the CPF orbit for a week, 3D differences between the results and the final orbit from the GFZ AC were less than 56.001 m for one day. Since the accuracy of the final orbit is known to be below the decimeter level, the accuracy of SLR-based predicted orbital ephemeris is applicable to the maintenance of GEO satellite orbits.

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