GNSS-based precise orbit determination for maneuvering LEO satellites

Abstract Maneuverability is essential for low Earth orbit (LEO) satellites to fulfill various operational objectives. However, the precise determination (POD) process might deteriorate due imperfect satellite orbital dynamics modeling. This article develops a generic POD strategy with maneuver handling LEO equipped high-performance spaceborne Global Navigation Satellite System (GNSS) receivers. Given time span of an executed maneuver, set constant thrust accelerations in body-fixed reference frame estimated without using a-priori accelerations. In addition, different numbers velocity pulses are at predefined epochs determined by duration maneuver. experiments done GRACE-FO and Sentinel-3 satellites, which maneuvers vary significantly. The orbits assessed via internal consistency checks external validations. Internally, each direction, agreement between reduced-dynamic kinematic reaches level 1 cm, comparable day maneuvers. Externally, comparisons official products from Copernicus Quality Working Group confirm reliability new handling. Finally, laser ranging K-band measurements indicate 1-cm accuracy absolute 2-mm relative orbits. tested Bernese GNSS Software, consistently developed Astronomical Institute University Bern.