Abstract
Due to the cuboid satellite body of BeiDou-3 satellites, the accuracy of their orbit showed a trend of systematic variation with the sun-satellite-earth angle (ε) using the Extend CODE Orbit Model (ECOM1). Therefore, an a priori cuboid box-wing model (named the cuboid model) is necessary to compensate ECOM1. Considering that the body-dimensions and optical properties of the BeiDou-3 satellites used to construct the box-wing model have not yet been fully released, the adjustable box-wing model (ABW) was used for precise orbit determination (POD). The a priori cuboid box-wing model was directly estimated by the precision radiation accelerations, obtained from ABW POD. When using ECOM1 model, for 14 < β < 40°, a linear systematic variation of D0 related to the elevation of the sun above the orbital plane (β-angle) with a slope of 0.048 nm/s2/°, was found for C30. After adding the cuboid model to assist ECOM1 (named Cuboid + ECOM1), the slope was reduced to 0.005 nm/s2/°, and for C20 satellite, the standard deviation (STD) of D0 was improved, from 1.28 to 0.85 nm/s2 (34%). For satellite laser ranging (SLR) validation, when using the ECOM1 model, the systematic variation with the ε angle was about 14 cm for C20 and C30. After using the Cuboid + ECOM1 model, the variation was significantly reduced to about 5 cm. For C20 and C21, compared with the ECOM1 model, the root mean square (RMS) of the ECOM2 and Cuboid + ECOM1 model was improved by about 0.54 (10.3%) and 0.43 cm (8.7%). For C29 and C30, the RMS of ECOM2 and Cuboid + ECOM1 model was improved for about 0.7 (10.9%) and 1.6 cm (25.6%). Finally, the RMS of the SLR residuals of 4.37 to 4.88 cm was achieved for BeiDou-3 POD.
Highlights
The construction of the BeiDou-3 global navigation system began in November 2017
For the Galileo and Quasi Zenith Satellite System (QZSS) satellites, the satellite laser ranging (SLR) validation results of the orbits indicate that there is a systematic error associated with the elevation of the sun above the orbital plane (β-angle), when the ECOM1 model is adopted for precise orbit determination (POD)
The main dimensions of Shanghai Engineering Center for Microsatellites (SECM) satellites are more cuboid than the BeiDou-2 satellites [19,20], and from the POD from the ECOM1 model, we found that the solar radiation acceleration of the BeiDou-3 Medium Earth Orbit (MEO) satellites incurs systematic errors with respect to the β-angle, which was not found for the BeiDou-2 MEO satellite
Summary
The construction of the BeiDou-3 global navigation system began in November 2017. As of April 2019, 18 Medium Earth Orbit (MEO) satellites, one Geostationary Orbit (GEO) satellite, and one Inclined Geosynchronous Orbit (IGSO) satellite were launched into orbit. Extending the CODE Orbit model (ECOM1) with five parameters (D0, Y0, B0, Bc, and Bs) produces an empirical SRP model, which is simple and does not require an a priori model It was widely adopted for the SRP of GPS and GLONASS for the most of Multi-GNSS Experiment (MGEX) analysis centers [3,4,5]. In the absence of this information, the accuracy of the box-wing SRP model was limited In this case, Rodriguez-Solano et al developed an adjustable box-wing model (ABW) for GPS satellites, which directly estimates the optical properties, and obtained a comparable result to that using the ECOM1 model [14,15]. An a priori cuboid box-wing model is necessary to improve the accuracy of POD Based on this background, through precise orbit determination using the ABW model, we obtained the precise solar radiation accelerations. The performance of the a priori cuboid box-wing model was validated by the orbit accuracy and clock offset
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