A New Approach for Pure Kinematical and Reduced-Kinematical Determination of LEO Orbit Based on GNSS Observations

  • A. ShabanlouiEmail author
  • K. H. Ilk
Conference paper
Part of the International Association of Geodesy Symposia book series (IAG SYMPOSIA, volume 136)


The geometrical point-wise satellite positions of a Low Earth Orbiter (LEO) equipped with a Global Navigation Satellite System (GNSS) receiver can be derived by GNSS analysis techniques based on hl-SST (high-low Satellite to Satellite Tracking) observations. In the geometrically determined LEO orbit, there is no connection between subsequent positions, and consequently, no information about the velocity and the acceleration or in general kinematical information of the satellite is available. If the kinematical parameters which consistently connects positions, velocities and accelerations are determined by a best fitting process based on the observations, we perform a pure Kinematical Precise Orbit Determination (KPOD). In addition, the proposed approach has a capability to use certain dynamical constraints based on the dynamical force function model. In this case, we introduce a Reduced-Kinematical Precise Orbit Determination (RKPOD) of a specific level depending on the strength of the “dynamical constraints”. The various possibilities and the corresponding results of CHAMP orbits based on GNSS observations are presented.


Global Navigation Satellite System Global Navigation Satellite System Orbit Determination Precise Orbit Determination Dynamical Restriction 
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We gratefully acknowledge the financial support of the BMBF under the project ”REAL-GOCE”.


  1. Abramowitz M, Stegun IA (1972) Handbook of mathematical functions with formulas, graphs, and mathematical tables. Dover, New YorkGoogle Scholar
  2. Klose U (1985). Beiträge zur Lösung einer Integralgleichung vom HAMMERSTEINschen Typ. Diploma Thesis, TUM, GermanyGoogle Scholar
  3. Ilk KH (1977) Berechnung von Referenzbahnen durch Lösung selbstadjungierter Randwertaufgaben, DGK, Reihe C, Heft 228, Munich, GermanyGoogle Scholar
  4. Jäggi A (2007) Pseudo-stochastic orbit modeling of low earth satellites using the GPS. Ph.D. Thesis, University of Bern, SwitzerlandGoogle Scholar
  5. Mayer-Gürr T (2006) Gravitationsfeldbestimmung aus der Analyse kurzer Bahnbögen am Beispiel der Satellitenmission CHAMP und GRACE. Ph.D. Thesis, IGG, University of Bonn, GermanyGoogle Scholar
  6. Reigber C (1969) Zur Bestimmung des Gravitationsfeldes der Erde aus Satellitenbeobachtungen, DGK, Reihe C, Heft Nr. 137, Munich, GermanyGoogle Scholar
  7. Schneider M (1968) A general method of orbit determination. Ph.D. Thesis, Ministry of Technology, Farnborough, EnglandGoogle Scholar
  8. Shabanloui A (2008) A new approach for a kinematic-dynamic determination of low satellite orbits based on GNSS observations. Ph.D. Thesis, IGG, University of Bonn, GermanyGoogle Scholar
  9. Švehla D, Rothacher M (2003) Kinematic, reduced-kinematic, dynamic and reduced-dynamic precise orbit determination in the LEO orbit, 2nd CHAMP Science Meeting, Potsdam, GermanyGoogle Scholar

Copyright information

© Springer-Verlag Berlin Heidelberg 2012

Authors and Affiliations

  1. 1.Institute of Geodesy and GeoinformationUniversity of BonnBonnGermany

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