2008
DOI: 10.2478/v10018-009-0006-7
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Simplification of Geopotential Perturbing Force Acting on A Satellite

Abstract: Simplification of Geopotential Perturbing Force Acting on A SatelliteOne of the aspects of geopotential models is orbit integration of satellites. The geopotential acceleration has the largest influence on a satellite with respect to the other perturbing forces. The equation of motion of satellites is a second-order vector differential equation. These equations are further simplified and developed in this study based on the geopotential force. This new expression is much simpler than the traditional one as it … Show more

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Cited by 7 publications
(3 citation statements)
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“…We simulated a three-month orbit of GOCE using the strategy used by Eshagh et al (2009) with an orbit integration step size of 5 s corresponding to a spatial resolution of 38.5 km. GOCE is flying over Fennoscandia with maximum and minimum altitude of 256 km and 231 km, respectively.…”
Section: Recovery From On-orbit T Rrmentioning
confidence: 99%
“…We simulated a three-month orbit of GOCE using the strategy used by Eshagh et al (2009) with an orbit integration step size of 5 s corresponding to a spatial resolution of 38.5 km. GOCE is flying over Fennoscandia with maximum and minimum altitude of 256 km and 231 km, respectively.…”
Section: Recovery From On-orbit T Rrmentioning
confidence: 99%
“…In the paper of Eshagh et al (2009), non-singular expressions are constructed for the geopotential derivatives of the first order in the quasi-inertial reference frame. It is possible to transform these expressions to TRF.…”
Section: First-order Derivativesmentioning
confidence: 99%
“…Su (2000), Wolf (2000), Eshagh (2003Eshagh ( , 2005Eshagh ( , 2009a, Najafi-Alamdari (2006 and2007) and Somodi and Földvary (2011). Eshagh et al (2009) simplified the mathematical formulae of equations of motion of satellites and applied them for a study on the orbit integration of GOCE, the gravity field recovery and climate experiment (GRACE) (Tapley et al 2005) and the Challenging Minisatellite Payload (CHAMP) (Reigber et al 1999 and missions. In all methods for orbit determination, the acceleration of the satellite should be computed before the integration process using the force models.…”
Section: Introductionmentioning
confidence: 99%