Ephemeris errors of GPS satellites

Ephemeris errors are supposed to be a major factor limiting the usefulness ofGPS in high precision geodesy. Considerations of orbital mechanics suggest that, regardless of their complexity, the uncertainties in the solar radiation pressure model, the gravity field model, and the estimated initial state, may have simple effects on the ephemeris. This possibility has been tested by fitting linear combinations of simple functions—chosen on theoretical grounds—to simulated errors of three-day ephemerides. With a set of five functions for the across-track component, six for the radial, and seven for the along-track, it has been possible to fit the position errors to better than 1% of theirr.m.s values, in all the caces studied. The simulations included —besides solar radiation pressure errors—gravity field model and initial state uncertainties, as well as an unknown constant force along the axis of the solar panels. The solar radiation force was calculated taking into account the shape, orientation, and physical properties (reflectivity and specularity) of the main parts of the spacecraft, under various conditions of illumination (continuous sunlight, eclipses, etc.).