URE and URA for predicted LEO satellite orbits at different altitudes

In recent years, low Earth orbit (LEO) satellites have been frequently discussed for their benefits in positioning and navigation services as an augmentation to the global satellite systems (GNSSs). Similar concept based on ranging GNSS satellites, precise of single-receiver users needs high-accuracy orbits clocks LEO a pre-condition. For real-time users, high prediction accuracies these at different latencies are needed. Unlike clocks, can be typically predicted hours with accuracy. however, face more complicated perturbing dynamic terms due altitudes. Therefore, accuracy integrity need addressed. this study, using real data three test GRACE C, Sentinel-1A Sentinel-3B altitudes, various reduced-dynamic strategies assessed, appropriate methods selected times up 6 h. The global-averaged orbital user range errors (OUREs) shown altitude-related. 700–800 km Sentinel 500 satellite, RMS OUREs is sub-dm dm-level time 1 h, respectively, around 0.2 m 0.6 respectively. purposes, worst-location OURE calculated proposed algorithm considering Ellipsoid, not sphere usually done satellites. (OURA) then evaluated periods, having time-dependent model compute overbounding OURA any within With risk 10-5, hourly quadratic polynomials model, 0.1 sub-meter level h