Position and velocity perturbations for the determination of geopotential from space geodetic measurements

Details Position and velocity perturbations for the determination of geopotential from space geodetic measurements Position and velocity perturbations for the determination of geopotential from space geodetic measurements

Mar 2008

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=2008cemda.100..231x&link_type=abstract

Celestial Mechanics and Dynamical Astronomy, Volume 100, Issue 3, pp.231-249

Astronomy and Astrophysics

Astronomy

6

Coordinate Perturbation, Geopotential, Satellite-To-Satellite Tracking (Sst), Satellite Geodesy, Velocity Perturbation, Leo Satellites

Scientific paper

Although space geodetic observing systems have been advanced recently to such a revolutionary level that low Earth Orbiting (LEO) satellites can now be tracked almost continuously and at the unprecedented high accuracy, none of the three basic methods for mapping the Earth’s gravity field, namely, Kaula linear perturbation, the numerical integration method and the orbit energy-based method, could meet the demand of these challenging data. Some theoretical effort has been made in order to establish comparable mathematical modellings for these measurements, notably by Mayer-Gürr et al. (J Geod 78:462-480, 2005). Although the numerical integration method has been routinely used to produce models of the Earth’s gravity field, for example, from recent satellite gravity missions CHAMP and GRACE, the modelling error of the method increases with the increase of the length of an arc. In order to best exploit the almost continuity and unprecedented high accuracy provided by modern space observing technology for the determination of the Earth’s gravity field, we propose using measured orbits as approximate values and derive the corresponding coordinate and velocity perturbations. The perturbations derived are quasi-linear, linear and of second-order approximation. Unlike conventional perturbation techniques which are only valid in the vicinity of reference mean values, our coordinate and velocity perturbations are mathematically valid uniformly through a whole orbital arc of any length. In particular, the derived coordinate and velocity perturbations are free of singularity due to the critical inclination and resonance inherent in the solution of artificial satellite motion by using various types of orbital elements. We then transform the coordinate and velocity perturbations into those of the six Keplerian orbital elements. For completeness, we also briefly outline how to use the derived coordinate and velocity perturbations to establish observation equations of space geodetic measurements for the determination of geopotential.

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