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The celestial mechanics approach: application to data of the GRACE mission

Beutler, Gerhard ; Jäggi, Adrian ; Mervart, Leoš ; Meyer, Ulrich

In: Journal of Geodesy, 2010, vol. 84, no. 11, p. 661-681

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    Titre
    • The celestial mechanics approach: application to data of the GRACE mission
    Auteur
    • Beutler, Gerhard. Astronomical Institute, University of Bern, Sidlerstrasse 5, 3012, Bern, Switzerland
    • Jäggi, Adrian. Astronomical Institute, University of Bern, Sidlerstrasse 5, 3012, Bern, Switzerland
    • Mervart, Leoš. Institute of Advanced Geodesy, Czech Technical University, K-152, FSvCVVT Thakurova 7, 16629, Prague 6-Dejvice, Czech Republic
    • Meyer, Ulrich. Astronomical Institute, University of Bern, Sidlerstrasse 5, 3012, Bern, Switzerland
    Type de document
    • Postprint
    Identifiant OAI-PMH
    • oai:doc.rero.ch:311524
    Summary
    The celestial mechanics approach (CMA) has its roots in the Bernese GPS software and was extensively used for determining the orbits of high-orbiting satellites. The CMA was extended to determine the orbits of Low Earth Orbiting satellites (LEOs) equipped with GPS receivers and of constellations of LEOs equipped in addition with inter-satellite links. In recent years the CMA was further developed and used for gravity field determination. The CMA was developed by the Astronomical Institute of the University of Bern (AIUB). The CMA is presented from the theoretical perspective in (Beutler etal. 2010). The key elements of the CMA are illustrated here using data from 50 days of GPS, K-Band, and accelerometer observations gathered by the Gravity Recovery And Climate Experiment (GRACE) mission in 2007. We study in particular the impact of (1) analyzing different observables [Global Positioning System (GPS) observations only, inter-satellite measurements only], (2) analyzing a combination of observations of different types on the level of the normal equation systems (NEQs), (3) using accelerometer data, (4) different orbit parametrizations (short-arc, reduced-dynamic) by imposing different constraints on the stochastic orbit parameters, and (5) using either the inter-satellite ranges or their time derivatives. The so-called GRACE baseline, i.e., the achievable accuracy of the GRACE gravity field for a particular solution strategy, is established for the CMA