
320 T. Schöne et al.
Table 1 The main models, input data and corrections used for the RA satellite orbit determination
Forces, input data, corrections Model used
Geopotential EIGEN-GRACE04Sp up to n = m = 80 (70 for
TOPEX/Poseidon) (Foerste et al., 2008)
Third body gravitational attraction Sun, Moon, Mercury, Venus, Mars, Jupiter, Saturn
(DE405, LE405) (Standish, 1998)
Atmosphere density MSIS-86 (Hedin, 1987), CLS F10.7 cm solar flux and
Ap coefficients
Solar radiation pressure Umbra, penumbra modeled
Albedoandinfraredradiationof
the Earth
Knocke and Ries (1987)
Solid Earth tides IERS Conventions 2003 (McCarthy and Petit, 2003)
Ocean tides FES2004, up to n = m = 50 (Letellier, 2004)
Atmospheric tides Biancale and Bode (2006)
Earth rotation parameters IERS EOP 05 C04 series with IERS2003 daily and
sub-daily corrections
(http://www.iers.org/MainDisp.csl?pid=36-9)
Nutation model Wahr model with VLBI corrections (McCarthy and
Petit, 2003)
Initial station coordinates ITRF2000, if available, or estimated
Station velocities ITRF2000, if available, or NNR-NUVEL1A model
Troposphere correction Marrini-Murray (1973) with Herring correction for SLR
data, Hopfield (1969) model for Doppler and DORIS
data
Ocean loading effect on stations GFZ, based on FES2004 ocean tide model
Atmospheric loading effect on
stations
GFZ, based on ECMWF atmosphere data
Relativistic corrections Post-Newtonian correction, relativistic corrections for
SLR measurements (McCarthy and Petit, 2003)
The 7-day orbital arcs with 2-day overlaps were used for GEOSAT, ERS-1 and
ERS-2 and 12-day arcs for TOPEX/Poseidon. Shorter arcs were used in case of
orbit maneuvers. The orbit quality was evaluated using root mean square (RMS)
fits of measurements, orbital arc overlaps, RMS and mean crossover differences.
The use of the new models, in particular the EIGEN-GRACE geopotential models
(Flechtner et al., 2006) and an optimal parameterization for each satellite (Rudenko
and Schöne, 2007) allowed improving the satellite orbits significantly (Rudenko
et al., 2006, 2007), as compared to the orbits derived in the standard distribution
of altimetry data. As a result, e.g., the mean value of RMS crossover differences
reduces from 11.7 cm for ERS-2 orbit derived using PGM055 geopotential and
other rather old models (Massmann et al., 1997) to 7.1 cm for the new orbit.
Improved parameterization and new models also significantly enhance the GEOSAT
orbit, especially for the period of high solar activity (MJD 47,400–47,900) (Fig. 3).
The mean value of RMS crossover differences is 15.4 cm for NASA JGM-3 orbit
(GEOSAT Handbook, 1997) and 9.0 cm for GFZ EIGEN-GRACE04S orbit of
GEOSAT.